Airworthiness Directives; General Electric Company Turbofan Engines, 63307-63311 [2014-24697]
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Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations
63307
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
required in paragraph (f)(1) of this AD, at the
next scheduled maintenance inspection or
within the next 150 hours TIS, whichever
occurs later, replace the control column with
an airworthy P/N 08–45031/32.
Issued in Kansas City, Missouri, on
October 9, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(g) Other FAA AD Provisions
[FR Doc. 2014–24698 Filed 10–22–14; 8:45 am]
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4123; fax: (816)
329–4090; email: karl.schletzbaum@faa.gov.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
BILLING CODE 4910–13–P
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2014–21–02 Pacific Aerospace Limited:
Amendment 39–17994; Docket No.
FAA–2014–0532; Directorate Identifier
2014–CE–016–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective November 28, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pacific Aerospace
Limited Models FU24–954 and FU24A–954
airplanes, all serial numbers, certificated in
any category.
(d) Subject
Air Transport Association of America
(ATA) Code 27: Flight Controls.
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(e) Reason
This AD was prompted from mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as cracking of
the control column at the wiring access hole.
We are issuing this AD to detect and correct
cracking of the control column at the wiring
access hole, which could cause control
column failure and subsequent loss of
control.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) through (f)(3) of
this AD, following the accomplishment
instructions in Pacific Aerospace Limited
Mandatory Service Bulletin PACSB/FU/095,
Issue 2, dated May 28, 2014.
(1) Within the next 50 hours time-inservice (TIS) after November 28, 2014 (the
effective date of this AD), inspect the control
column part number (P/N) 08–45031/32 for
cracks.
(2) If any mechanical damage, deformation,
or cracks are found, before further flight,
replace the control column with an airworthy
control column P/N 08–45031/32.
(3) If no mechanical damage, deformation,
or cracks are found after the inspection
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(h) Related Information
Refer to MCAI Civil Aviation Authority
(CAA) AD DCA/FU24/183, dated May 29,
2014, for related information. The MCAI can
be found in the AD docket on the Internet at:
https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0532-0002.
(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) Pacific Aerospace Limited Mandatory
Service Bulletin PACSB/FU/095, Issue 2,
dated May 28, 2014.
(ii) Reserved.
(3) For Pacific Aerospace Limited service
information identified in this AD, contact
Pacific Aerospace Limited, Airport Road,
Hamilton Private Bag 3027 Hamilton 3240,
New Zealand; telephone: +64 7 843 6144; fax:
+64 7 843 6134; email: pacific@
aerospace.co.nz; Internet: https://
www.aerospace.co.nz/.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28413; Directorate
Identifier 2007–NE–25–AD; Amendment 39–
17993; AD 2014–21–01]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directives (ADs) 90–26–
01, 91–20–02, and 2009–05–02 for all
General Electric Company (GE) CF6–
80C2 and CF6–80E1 series turbofan
engines. This AD retains the
requirements of those ADs and requires
removal of additional fuel manifold part
numbers (P/Ns), additional repetitive
inspections, replacement as required of
certain fuel manifold P/Ns and tube
(block) clamps, and replacement of loop
clamps. This AD was prompted by a
report of an under-cowl fire caused by
a manifold high-pressure fuel leak, and
several additional reports of fuel leaks.
We are issuing this AD to prevent
failure of the fuel manifold, which
could lead to uncontrolled engine fire,
engine damage, and damage to the
airplane.
DATES: This AD is effective November
28, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 28, 2014.
ADDRESSES: For service information
identified in this AD, contact General
Electric Company, GE Aviation, Room
285, 1 Neumann Way, Cincinnati, OH
45215; phone: (513) 552–3272; email:
geae.aoc@ge.com. You may view this
service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call (781) 238–
7125.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations
www.regulations.gov by searching for
and locating Docket No. FAA–2007–
28413; 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 Document 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:
Kasra Sharifi, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone (781) 238–7773; fax: (781) 238–
7199; email: kasra.sharifi@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 90–26–01,
Amendment 39–6810 (55 FR 49611,
November 30, 1990), (‘‘AD 90–26–01’’),
and AD 91–20–02, Amendment 39–8036
(56 FR 55231, October 25, 1991), (‘‘AD
91–20–02’’), and AD 2009–05–02,
Amendment 39–15826 (74 FR 8161,
February 24, 2009), (‘‘AD 2009–05–02’’).
AD 90–26–01 and AD 91–20–02 applied
to all GE CF6–80C2 series turbofan
engines. AD 2009–05–02 applied to all
GE CF6–80C2 and CF6–80E1 series
turbofan engines. The NPRM published
in the Federal Register on January 17,
2014 (79 FR 3139). The NPRM was
prompted by a report of an under-cowl
fire caused by a manifold high-pressure
fuel leak and several additional reports
of fuel leaks. The NPRM proposed to
retain the requirements of the
superseded ADs: AD 90–26–01 and AD
91–20–02 required removal of certain
fuel manifold P/Ns; AD 2009–05–02
required inspection of certain fuel
manifold P/Ns and replacement of
certain consumable components. The
NPRM also proposed to require removal
of additional fuel manifold P/Ns,
performance of additional initial and
repetitive inspections, replacement as
required of certain fuel manifold P/Ns
and tube (block) clamps, and
replacement of loop clamps at each fuel
manifold inspection opportunity. We
are issuing this AD to prevent failure of
the fuel manifold, which could lead to
uncontrolled engine fire, engine
damage, and damage to the airplane.
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15:42 Oct 22, 2014
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 3139,
January 17, 2014) and the FAA’s
response to each comment.
Request To Replace Two Incorrect Part
Numbers
Several commenters requested that we
replace two incorrect fuel manifold
P/Ns with the correct P/Ns.
We agree. We corrected the P/Ns in
paragraph (c) of this AD from P/Ns
1308M31G12 and 1308M32G12 to P/Ns
1303M31G12 and 1303M32G12.
Request To Change and Clarify
Compliance Information
Several commenters requested that we
make changes to Table 1 to paragraph
(e) in the NPRM (79 FR 3139, January
17, 2014). Three commenters requested
that we remove the compliance time of
six months because this requirement is
unjustified. Two commenters requested
that we remove one row of information
due to redundancy. One commenter
requested that we reorder the rows to
make the table easier to follow.
We partially agree. We agree that the
table is problematic. A six-month
compliance time was meant to be a
‘‘grace period’’ for products that might
have already exceeded the threshold.
But, including a ‘‘grace period’’ is
unnecessary, since AD 2009–05–02,
which we are superseding with this AD,
mandates the same requirement. We
removed the six-month compliance time
period.
We disagree with making the other
changes as suggested, but did reword
paragraph (e) to this AD to eliminate the
tables and clarify the AD.
Request To Change Definition of Shop
Visit
Several commenters requested that we
change the definition of shop visit to
exclude certain maintenance visits
because the current definition forces the
replacement of the fuel manifold at the
majority of shop visits.
We agree. We changed the definition
of shop visit for the purposes of this AD
to exclude shop visits for specified
types of maintenance.
Request To Allow Reinstallation of
Certain P/N Fuel Manifolds During OnWing Maintenance
Virgin Atlantic Airways, Delta Air
Lines, AIRDO, and GE requested that we
allow reinstallation of fuel manifolds,
P/Ns 1303M31G12, 1303M32G12,
2420M70G01, and 2420M71G01, during
on-wing maintenance, and only
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mandate removal of these P/Ns during
shop visits. The commenters state that
modification of the fuel manifold
configuration during on-wing
maintenance is not practicable due to
complexity, potential for maintenance
error, and cost compared to replacement
during shop visit.
We agree. The intent of this AD is to
require removal of fuel manifolds, P/Ns
1303M31G12, 1303M32G12,
2420M70G01, and 2420M71G01, during
shop visit, not during on-wing
maintenance. We removed the
installation prohibition statement that
included these P/Ns.
Request To Exclude Certain Engine
Models From Applicability
Lufthansa Cargo requested that we
exclude from the applicability of this
AD certain CF6–80C2 engine models.
We disagree. All CF6–80C2 engine
models are affected by the same unsafe
condition. We did not change this AD.
Request To Change the Focus of This
AD, and To Retain and Supersede
Different ADs
KLM Royal Dutch Airlines (KLM)
requested that we address pigtail
cracking in this AD, instead of tube
(block) clamp and loop clamp chafing,
by retaining AD 2009–05–02,
Amendment 39–15826 (74 FR 8161,
February 24, 2009), AD 91–20–02,
Amendment 39–8036 (56 FR 55231,
October 25, 1991), and AD 90–26–01,
Amendment 39–6810 (55 FR 49611,
November 30, 1990), and by
superseding AD 2007–11–20,
Amendment 39–15077 (72 FR 30956,
June 5, 2007). KLM states that the recent
under-cowl fire event was related to
pigtail cracking, which the FAA has not
addressed, and not to tube (block) and
loop clamp chafing.
We disagree. Pigtail cracking, tube
(block) clamp chafing, and loop clamp
chafing can all be caused by resonant
vibration within the engine operation
range. This AD requires removal of fuel
manifolds susceptible to resonant
vibration, which addresses pigtail
cracking, tube (block) clamp chafing,
and loop clamp chafing leading to fuel
manifold leaks. We did not change this
AD.
Request To Remove From Paragraph
(e)(2) Reference to ‘‘Tube (Block)
Clamp’’
KLM requested that we delete
reference to the ‘‘Tube (Block) Clamp’’
from paragraph (e)(2) of this AD because
instructions regarding inspection and
replacement of the tube (block) clamp
are not addressed in that paragraph.
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We partially agree. The reference to
the ‘‘Tube (Block) Clamp’’ in paragraph
(e)(2) is inaccurate. We restructured the
compliance paragraphs. Paragraphs
(e)(2)(ii) and (e)(2)(iii) of this AD now
reference ‘‘Tube (Block) Clamp.’’
Request To Provide More Information
Regarding the Unsafe Condition
Lufthansa Technik AG and Deutsche
Lufthansa AG requested that we provide
additional details concerning the unsafe
condition.
We partially agree. Although the AD
Discussion section provides sufficient
information regarding the fuel manifold
leaks, we included a reference to
additional information in the Related
Information paragraph of this AD.
Request To Expand Compliance To
Address Other Unsafe Conditions
One commenter requested that we
expand the compliance requirements of
this AD to address other possible unsafe
conditions in the designs of the
accessory gearbox, spray shield, and
fuel nozzle, and made reference to
National Transportation Safety Board
(NTSB) safety recommendations (SRs)
A–13–022 and A–12–047.
We disagree. Unsafe conditions in the
engine caused by designs of the
accessory gearbox and spray shield are
not the subjects of this AD. Fire caused
by fuel manifold leak is the subject of
this AD. SRs A–13–022 and A–12–047
do not address fire caused by fuel
manifold leaks. We did not change this
AD.
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Request To Allow Use of Future
Revisions of Referenced Service
Bulletins (SBs)
Delta Air Lines requested that we
allow use of future revisions of the SBs
referenced in compliance paragraphs
because this would eliminate the need
to request an alternative method of
compliance (AMOC) if the SBs are
revised.
We disagree. We are authorized to
mandate use of procedures in SBs that
are published and which we have
reviewed. Since future revisions of SBs
are not yet published, we are not
authorized to mandate their use in
advance. We did not change this AD.
Request To Address Repetitive
Inspections of Fuel Manifolds Repaired
With PTFE-Coated Para-Aramid Tape
Japan Airlines requested that we
allow repetitive inspections of fuel
manifolds that have PTFE-coated paraaramid tape at the tube (block) clamp
locations. The NPRM (79 FR 3139,
January 17, 2014) addressed initial
inspections, but did not address
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15:42 Oct 22, 2014
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repetitive inspections of fuel manifolds
repaired with PTFE-coated para-aramid
tape.
We agree. We changed the references
to SBs in this AD to more recent
versions that allow repetitive
inspections of fuel manifolds that have
PTFE-coated para-aramid tape at the
tube (block) clamp locations.
Request To Require the Use of GE
Method To Replace Fuel Manifolds
Boeing Commercial Airplanes and
another commenter requested that we
require that manifolds be replaced using
the method stated in the GE SBs. To
substantiate the request, the second
commenter referred to NTSB SR A–13–
028.
We disagree. The regulations require
that operators use acceptable methods,
techniques, and practices to replace the
fuel manifolds. The GE SBs contain one
acceptable method to replace the fuel
manifolds, but not the only acceptable
method of doing so. We did not change
this AD.
Request To Clarify Certain Preamble
and Compliance Paragraphs
GE requested that we clarify, in the
‘‘Proposed AD Requirements’’
paragraph, the additional P/Ns of fuel
manifolds to be inspected and replaced.
GE also requested that we make clear, in
the ‘‘Summary’’ paragraph, that on-wing
replacement of tube (block) clamps and
fuel manifolds is based on inspection
results. GE also requested that we use
alternative wording in paragraph (e) and
Table 2 to paragraph (e) of this AD.
We partially agree. We agree that we
needed to clarify the P/Ns to be
removed before further flight, and those
to be inspected until removed. We
changed this AD to clearly identify both
groups. We also agree that paragraph (e)
of this AD required clarification. We
reworded paragraph (e) of this AD to
clearly identify the requirements to
correct the unsafe condition.
Request To Allow Installation of
Certain Prohibited P/Ns
Asiana Airlines, EVA Airways, Thai
Airways, AIRDO, and Japan Airlines
requested that for fuel manifold, P/Ns
1303M31G12, 1303M32G12,
2420M70G01, and 2420M71G01, we
reduce the inspection interval or require
non-destructive inspection at shop visits
rather than require removal and prohibit
installation. The operators state that
their records do not indicate that these
parts cause leaks or experience wear
that would cause their replacement, and
they expressed concerns that the
reliability of the replacement fuel
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63309
manifolds is lower than that of the
prohibited fuel manifolds.
We disagree. A reduced inspection
interval does not prevent pigtail
cracking between shop visits. Our data
does not justify a reduced inspection
interval to prevent fuel leak events, or
indicate that the new fuel manifold
design has lower reliability. We did not
change this AD.
Request To Allow Use of Certain P/Ns
for Drained Engine Configurations
Lufthansa Technik AG requested that
we allow the use of fuel manifold, P/Ns
2420M70G01, 2420M71G01,
1303M31G12, and 1303M32G12, as
replacement parts for drained (pre SB
73–0253) engine configurations. The
commenter states that GE’s service
information allows use of fuel manifold,
P/Ns 1303M31G12 and 1303M32G12,
on engines with drain system installed,
and this AD does not prohibit
installation of fuel manifold, P/Ns
1303M31G10 and 1303M32G10.
We disagree. We have no data
showing that drainless fuel manifolds
installed in engines with a drain system
are more reliable than when installed in
engines with a drainless system. We did
not change this AD.
Request To Remove Certain Fuel
Manifolds From Applicability
Lufthansa Cargo requested that we
remove from the applicability of this AD
drainless fuel manifolds to which PTFEcoated para-aramid tape was applied
and the loop and tube (block) clamps
were inspected.
We disagree. We received several
reports of fuel leaks and a report of
under-cowl fire. The inspections alone
required by this AD do not address
pigtail cracking leading to fuel leaks,
and therefore do not provide an
acceptable level of safety. We did not
change this AD.
Request To Remove the Word
‘‘Uncontrolled’’ From the Description of
Fire
Boeing Commercial Airplanes
requested that we remove from the
preamble the word ‘‘uncontrolled’’ from
the description of fire caused by a fuel
manifold leak because an uncontrolled
fire in this scenario could only occur
with a significant failure of the engine
nacelle fire protection system.
We disagree. The data upon which we
relied, including the Continued
Airworthiness Assessment
Methodologies (CAAM) database for
transport category airplanes, includes
data showing flammable fluid leaks
leading to uncontrolled fires. We did
not change this AD.
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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 editorial changes to improve clarity.
We have determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR 3139,
January 17, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 3139,
January 17, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD would affect
1,126 engines installed on airplanes of
U.S. registry. We also estimate that
required parts cost about $34,894 per
engine. We also estimate that it will take
about 6 hours to accomplish the actions
required by this AD. The average labor
rate is $85 per hour. Based on these
figures, we estimate the total cost of this
AD to U.S. operators to be $39,864,904.
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
We have determined that 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.
15:42 Oct 22, 2014
Jkt 235001
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Authority for This Rulemaking
VerDate Sep<11>2014
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 to the extent that it justifies
making a regulatory distinction, 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.
[Amended]
2. The FAA amends § 39.13 by:
a. Removing airworthiness directive
(AD) 90–26–01, Amendment 39–6810
(55 FR 49611, November 30, 1990); AD
91–20–02, Amendment 39–8036 (56 FR
55231, October 25, 1991); and AD 2009–
05–02, Amendment 39–15826 (74 FR
8161, February 24, 2009); and
■ b. Adding the following new AD:
■
■
2014–21–01 General Electric Company:
Amendment 39–17993; Docket No.
FAA–2007–28413; Directorate Identifier
2007–NE–25–AD.
(a) Effective Date
This AD is effective November 28, 2014.
(b) Affected ADs
This AD supersedes AD 90–26–01,
Amendment 39–6810 (55 FR 49611,
November 30, 1990); AD 91–20–02,
Amendment 39–8036 (56 FR 55231, October
25, 1991); and AD 2009–05–02, Amendment
39–15826, (74 FR 8161, February 24, 2009).
(c) Applicability
This AD applies to all General Electric
Company (GE) CF6–80C2 and CF6–80E1
series turbofan engines with fuel manifold,
part number (P/N) 1303M31G04,
1303M32G04, 1303M31G06, 1303M32G06,
1303M31G07, 1303M32G07, 1303M31G08,
1303M32G08, 1303M31G12, 1303M32G12,
2420M70G01, or 2420M71G01, installed.
(d) Unsafe Condition
This AD was prompted by a report of an
under-cowl fire caused by a fuel manifold
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high-pressure fuel leak, and several
additional reports of fuel leaks. We are
issuing this AD to prevent failure of the fuel
manifold, which could lead to uncontrolled
engine fire, engine damage, and damage to
the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) Fuel Manifold Removal.
(i) After the effective date of this AD, do
not return to service any CF6–80C2 or CF6–
80E1 series engine with fuel manifold P/N
1303M31G04, 1303M32G04, 1303M31G06,
1303M32G06, 1303M31G07, 1303M32G07,
1303M31G08, or 1303M32G08, installed.
(ii) At the next engine shop visit after the
effective date of this AD, remove from service
fuel manifold P/Ns 1303M31G12,
1303M32G12, 2420M70G01, and
2420M71G01.
(2) Fuel Manifold, Loop Clamp, and Tube
(Block) Clamp Initial and Repetitive
Inspection and Replacement.
(i) For CF6–80C2 and CF680E1 series
engines, with fuel manifold, P/N
1303M31G12, 1303M32G12, 2420M70G01, or
2420M71G01 installed, inspect the fuel
manifold and replace if required by
inspection results, and replace the loop
clamps as follows:
(A) For CF6–80C2 series engines, use
paragraphs 3.A, 3.C, and 3.D of GE CF6–80C2
Service Bulletin (SB) No. S/B 73–0326 R04,
Revision 4, dated December 23, 2009, to do
the inspection and replacements.
(B) For CF6–80E1 series engines, use
paragraphs 3.A, 3.B, and 3.C of GE CF6–80E1
SB No. S/B 73–0061 R04, Revision 4, dated
December 23, 2009, to do the inspection and
replacements.
(C) Compliance time for fuel manifold
inspection and loop clamp replacement:
(1) If the engine is a first-run engine,
inspect the fuel manifold and replace the
loop clamps within 7,500 flight hours (FH)
time-since-new (TSN).
(2) If the engine’s fuel manifold was ever
inspected and new loop clamps were
previously installed, inspect the fuel
manifold and replace the loop clamps within
7,500 FH time-since-last-inspection (TSLI).
(3) If the engine’s fuel manifold was not
inspected, new loop clamps were not
installed, or it is unknown when the loop
clamps were installed, inspect the fuel
manifold and replace the loop clamps within
1,750 FH time-since-last-shop-visit or within
4 months after the effective date of this AD,
whichever occurs later.
(ii) For CF6–80C2 and CF6–80E1 series
engines, with fuel manifold, P/N
1303M31G12, 1303M32G12, 2420M70G01, or
2420M71G01, with tube (block) clamp, P/N
1153M26G15, installed, inspect fuel
manifold and tube (block) clamps, and
replace if required by inspection results, as
follows:
(A) For CF6–80C2 series engines, use
paragraphs 3.A.(1) through 3.A.(8) and 3.C.(1)
through 3.C.(2) of GE CF6–80C2 SB No. S/B
73–0414, Revision 1, dated May 29, 2014, to
do the inspection.
(B) For CF6–80E1 series engines, use
paragraphs 3.A.(1) through 3.A.(6) and 3.C.(1)
E:\FR\FM\23OCR1.SGM
23OCR1
Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations
through 3.C.(2) of GE CF6–80E1 SB No. S/B
73–0121, Revision 1, dated May 29, 2014, to
do the inspection.
(C) Compliance time for fuel manifold and
tube (block) clamp inspection:
(1) If the engine is a first-run engine,
inspect the fuel manifold and tube (block)
clamps within 7,500 FH TSN or within 3
months after the effective date of this AD,
whichever occurs later.
(2) If the engine was previously inspected
using either of GE CF6–80C2 SB No. S/B 73–
0414, Revision 1, dated May 29, 2014, or GE
CF6–80E1 SB No. S/B 73–0121, Revision 1,
dated May 29, 2014, or earlier versions, then
inspect the fuel manifold and tube (block)
clamps within 7,500 FH TSLI or within 3
months after the effective date of this AD,
whichever occurs later.
(3) If the engine is not a first-run engine
and was not previously inspected using GE
CF6–80C2 SB No. S/B 73–0414, Revision 1,
dated May 29, 2014, or GE CF6–80E1 SB No.
S/B 73–0121, Revision 1, dated May 29,
2014, or earlier versions, then inspect the
fuel manifold and tube (block) clamps within
7,500 FH TSN or within 3 months after the
effective date of this AD, whichever occurs
later.
(iii) Thereafter, inspect fuel manifold, P/Ns
1303M31G12, 1303M32G12, 2420M70G01,
and 2420M71G01, and tube (block) clamps,
replace if required by inspection results, and
replace the loop clamps within every 7,500
FH TSLI, using paragraphs (e)(2)(i)(A),
(e)(2)(i)(B), (e)(2)(ii)(A), and (e)(2)(ii)(B) of
this AD, as applicable.
(f) Definition
(1) For the purposes of this AD, an engine
shop visit is the induction of an engine into
the shop where the separation of a major
engine flange occurs, except that induction
into the shop for any of the reasons in
paragraphs (f)(i) through (f)(iv) of this AD is
not an engine shop visit:
(i) Induction of an engine into a shop
solely for removal of the compressor top or
bottom case for airfoil maintenance, or for
variable stator vane bushing replacement;
(ii) Induction of an engine into a shop
solely for replacement of the turbine rear
frame;
(iii) Induction of an engine into a shop
solely for replacement of the accessory
gearbox or transfer gearbox, or both; or
(iv) Induction of an engine into a shop
solely for core vibration trim balance
procedure that requires separation of a major
engine flange.
(2) For the purposes of this AD, a first-run
engine is an engine that has not had a shop
visit since entering service.
wreier-aviles on DSK5TPTVN1PROD with RULES
(g) Alternative Methods of Compliance
(AMOCs)
(h) Related Information
DEPARTMENT OF TRANSPORTATION
(1) For more information about this AD,
contact Kasra Sharifi, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA. 01803;
phone (781) 238–7773; fax: (781) 238–7199;
email: kasra.sharifi@faa.gov.
(2) For additional details of the under cowl
fire that prompted this AD, refer to National
Transportation Safety Board (NTSB) safety
recommendation (SR) A–13–028. The NTSB
SR is available on the Internet at https://
www.ntsb.gov/doclib/recletters/2013/A-13028.pdf.
(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) General Electric Company (GE) CF6–
80C2 Service Bulletin (SB) No. 73–0326 R04,
Revision 4, dated December 23, 2009.
(ii) GE CF6–80C2 SB No. S/B 73–0414,
Revision 1, dated May 29, 2014.
(iii) GE CF6–80E1 SB No. 73–0061 R04,
Revision 4, dated December 23, 2009.
(iv) GE CF6–80E1 SB No. S/B 73–0121,
Revision 1, dated May 29, 2014.
(3) For GE service information identified in
this AD, contact General Electric Company,
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552–
3272; email: geae.aoc@ge.com.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, 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.
Issued in Burlington, Massachusetts, on
October 7, 2014.
Kim Smith,
Acting Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–24697 Filed 10–22–14; 8:45 am]
BILLING CODE 4910–13–P
(1) 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.
(2) Previously approved AMOCs for AD
2009–05–02 (74 FR 8161, February 24, 2009)
remain approved for the corresponding
requirements of paragraphs (e)(1) and (e)(2)
of this AD.
VerDate Sep<11>2014
15:42 Oct 22, 2014
Jkt 235001
PO 00000
63311
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0345; Directorate
Identifier 2013–NM–230–AD; Amendment
39–17998; AD 2014–21–06]
RIN 2120–AA64
Airworthiness Directives; Beechcraft
Corporation (Type Certificate
Previously Held by Hawker Beechcraft
Corporation; Raytheon Aircraft
Company; Beech Aircraft Corporation)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Beechcraft Corporation (Type Certificate
Previously Held by Hawker Beechcraft
Corporation; Raytheon Aircraft
Company; Beech Aircraft Corporation)
Model 400, 400A, 400T, and MU–300
airplanes. This AD was prompted by a
report of a failure of the Acme nut
threads in a pitch trim actuator (PTA).
This AD requires an inspection to
determine if PTAs having a certain
serial number and part number are
installed, and replacement if they are
installed. This AD also requires
repetitive replacements of PTAs with
new PTAs or certain overhauled PTAs.
We are issuing this AD to prevent
failure of the Acme nut threads in the
PTA, which could lead to loss of control
of pitch trim and reduced controllability
of the airplane.
DATES: This AD is effective November
28, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 28, 2014.
ADDRESSES: For service information
identified in this AD, contact Beechcraft
Corporation, TMDC, P.O. Box 85,
Wichita, KS 67201–0085; telephone
316–676–8238; fax 316–671–2540; email
tmdc@beechcraft.com; Internet https://
pubs.beechcraft.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.
SUMMARY:
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–2014–
Frm 00019
Fmt 4700
Sfmt 4700
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23OCR1
]]>Agencies
[Federal Register Volume 79, Number 205 (Thursday, October 23, 2014)]
[Rules and Regulations]
[Pages 63307-63311]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-24697]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28413; Directorate Identifier 2007-NE-25-AD;
Amendment 39-17993; AD 2014-21-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directives (ADs) 90-26-01,
91-20-02, and 2009-05-02 for all General Electric Company (GE) CF6-80C2
and CF6-80E1 series turbofan engines. This AD retains the requirements
of those ADs and requires removal of additional fuel manifold part
numbers (P/Ns), additional repetitive inspections, replacement as
required of certain fuel manifold P/Ns and tube (block) clamps, and
replacement of loop clamps. This AD was prompted by a report of an
under-cowl fire caused by a manifold high-pressure fuel leak, and
several additional reports of fuel leaks. We are issuing this AD to
prevent failure of the fuel manifold, which could lead to uncontrolled
engine fire, engine damage, and damage to the airplane.
DATES: This AD is effective November 28, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 28,
2014.
ADDRESSES: For service information identified in this AD, contact
General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552-3272; email: geae.aoc@ge.com.
You may view this service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For
information on the availability of this material at the FAA, call (781)
238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
[[Page 63308]]
www.regulations.gov by searching for and locating Docket No. FAA-2007-
28413; 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 Document 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: Kasra Sharifi, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone (781) 238-7773;
fax: (781) 238-7199; email: kasra.sharifi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 90-26-01, Amendment 39-6810 (55 FR 49611,
November 30, 1990), (``AD 90-26-01''), and AD 91-20-02, Amendment 39-
8036 (56 FR 55231, October 25, 1991), (``AD 91-20-02''), and AD 2009-
05-02, Amendment 39-15826 (74 FR 8161, February 24, 2009), (``AD 2009-
05-02''). AD 90-26-01 and AD 91-20-02 applied to all GE CF6-80C2 series
turbofan engines. AD 2009-05-02 applied to all GE CF6-80C2 and CF6-80E1
series turbofan engines. The NPRM published in the Federal Register on
January 17, 2014 (79 FR 3139). The NPRM was prompted by a report of an
under-cowl fire caused by a manifold high-pressure fuel leak and
several additional reports of fuel leaks. The NPRM proposed to retain
the requirements of the superseded ADs: AD 90-26-01 and AD 91-20-02
required removal of certain fuel manifold P/Ns; AD 2009-05-02 required
inspection of certain fuel manifold P/Ns and replacement of certain
consumable components. The NPRM also proposed to require removal of
additional fuel manifold P/Ns, performance of additional initial and
repetitive inspections, replacement as required of certain fuel
manifold P/Ns and tube (block) clamps, and replacement of loop clamps
at each fuel manifold inspection opportunity. We are issuing this AD to
prevent failure of the fuel manifold, which could lead to uncontrolled
engine fire, engine damage, and damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 3139, January 17, 2014) and the FAA's response to each comment.
Request To Replace Two Incorrect Part Numbers
Several commenters requested that we replace two incorrect fuel
manifold P/Ns with the correct P/Ns.
We agree. We corrected the P/Ns in paragraph (c) of this AD from P/
Ns 1308M31G12 and 1308M32G12 to P/Ns 1303M31G12 and 1303M32G12.
Request To Change and Clarify Compliance Information
Several commenters requested that we make changes to Table 1 to
paragraph (e) in the NPRM (79 FR 3139, January 17, 2014). Three
commenters requested that we remove the compliance time of six months
because this requirement is unjustified. Two commenters requested that
we remove one row of information due to redundancy. One commenter
requested that we reorder the rows to make the table easier to follow.
We partially agree. We agree that the table is problematic. A six-
month compliance time was meant to be a ``grace period'' for products
that might have already exceeded the threshold. But, including a
``grace period'' is unnecessary, since AD 2009-05-02, which we are
superseding with this AD, mandates the same requirement. We removed the
six-month compliance time period.
We disagree with making the other changes as suggested, but did
reword paragraph (e) to this AD to eliminate the tables and clarify the
AD.
Request To Change Definition of Shop Visit
Several commenters requested that we change the definition of shop
visit to exclude certain maintenance visits because the current
definition forces the replacement of the fuel manifold at the majority
of shop visits.
We agree. We changed the definition of shop visit for the purposes
of this AD to exclude shop visits for specified types of maintenance.
Request To Allow Reinstallation of Certain P/N Fuel Manifolds During
On-Wing Maintenance
Virgin Atlantic Airways, Delta Air Lines, AIRDO, and GE requested
that we allow reinstallation of fuel manifolds, P/Ns 1303M31G12,
1303M32G12, 2420M70G01, and 2420M71G01, during on-wing maintenance, and
only mandate removal of these P/Ns during shop visits. The commenters
state that modification of the fuel manifold configuration during on-
wing maintenance is not practicable due to complexity, potential for
maintenance error, and cost compared to replacement during shop visit.
We agree. The intent of this AD is to require removal of fuel
manifolds, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01,
during shop visit, not during on-wing maintenance. We removed the
installation prohibition statement that included these P/Ns.
Request To Exclude Certain Engine Models From Applicability
Lufthansa Cargo requested that we exclude from the applicability of
this AD certain CF6-80C2 engine models.
We disagree. All CF6-80C2 engine models are affected by the same
unsafe condition. We did not change this AD.
Request To Change the Focus of This AD, and To Retain and Supersede
Different ADs
KLM Royal Dutch Airlines (KLM) requested that we address pigtail
cracking in this AD, instead of tube (block) clamp and loop clamp
chafing, by retaining AD 2009-05-02, Amendment 39-15826 (74 FR 8161,
February 24, 2009), AD 91-20-02, Amendment 39-8036 (56 FR 55231,
October 25, 1991), and AD 90-26-01, Amendment 39-6810 (55 FR 49611,
November 30, 1990), and by superseding AD 2007-11-20, Amendment 39-
15077 (72 FR 30956, June 5, 2007). KLM states that the recent under-
cowl fire event was related to pigtail cracking, which the FAA has not
addressed, and not to tube (block) and loop clamp chafing.
We disagree. Pigtail cracking, tube (block) clamp chafing, and loop
clamp chafing can all be caused by resonant vibration within the engine
operation range. This AD requires removal of fuel manifolds susceptible
to resonant vibration, which addresses pigtail cracking, tube (block)
clamp chafing, and loop clamp chafing leading to fuel manifold leaks.
We did not change this AD.
Request To Remove From Paragraph (e)(2) Reference to ``Tube (Block)
Clamp''
KLM requested that we delete reference to the ``Tube (Block)
Clamp'' from paragraph (e)(2) of this AD because instructions regarding
inspection and replacement of the tube (block) clamp are not addressed
in that paragraph.
[[Page 63309]]
We partially agree. The reference to the ``Tube (Block) Clamp'' in
paragraph (e)(2) is inaccurate. We restructured the compliance
paragraphs. Paragraphs (e)(2)(ii) and (e)(2)(iii) of this AD now
reference ``Tube (Block) Clamp.''
Request To Provide More Information Regarding the Unsafe Condition
Lufthansa Technik AG and Deutsche Lufthansa AG requested that we
provide additional details concerning the unsafe condition.
We partially agree. Although the AD Discussion section provides
sufficient information regarding the fuel manifold leaks, we included a
reference to additional information in the Related Information
paragraph of this AD.
Request To Expand Compliance To Address Other Unsafe Conditions
One commenter requested that we expand the compliance requirements
of this AD to address other possible unsafe conditions in the designs
of the accessory gearbox, spray shield, and fuel nozzle, and made
reference to National Transportation Safety Board (NTSB) safety
recommendations (SRs) A-13-022 and A-12-047.
We disagree. Unsafe conditions in the engine caused by designs of
the accessory gearbox and spray shield are not the subjects of this AD.
Fire caused by fuel manifold leak is the subject of this AD. SRs A-13-
022 and A-12-047 do not address fire caused by fuel manifold leaks. We
did not change this AD.
Request To Allow Use of Future Revisions of Referenced Service
Bulletins (SBs)
Delta Air Lines requested that we allow use of future revisions of
the SBs referenced in compliance paragraphs because this would
eliminate the need to request an alternative method of compliance
(AMOC) if the SBs are revised.
We disagree. We are authorized to mandate use of procedures in SBs
that are published and which we have reviewed. Since future revisions
of SBs are not yet published, we are not authorized to mandate their
use in advance. We did not change this AD.
Request To Address Repetitive Inspections of Fuel Manifolds Repaired
With PTFE-Coated Para-Aramid Tape
Japan Airlines requested that we allow repetitive inspections of
fuel manifolds that have PTFE-coated para-aramid tape at the tube
(block) clamp locations. The NPRM (79 FR 3139, January 17, 2014)
addressed initial inspections, but did not address repetitive
inspections of fuel manifolds repaired with PTFE-coated para-aramid
tape.
We agree. We changed the references to SBs in this AD to more
recent versions that allow repetitive inspections of fuel manifolds
that have PTFE-coated para-aramid tape at the tube (block) clamp
locations.
Request To Require the Use of GE Method To Replace Fuel Manifolds
Boeing Commercial Airplanes and another commenter requested that we
require that manifolds be replaced using the method stated in the GE
SBs. To substantiate the request, the second commenter referred to NTSB
SR A-13-028.
We disagree. The regulations require that operators use acceptable
methods, techniques, and practices to replace the fuel manifolds. The
GE SBs contain one acceptable method to replace the fuel manifolds, but
not the only acceptable method of doing so. We did not change this AD.
Request To Clarify Certain Preamble and Compliance Paragraphs
GE requested that we clarify, in the ``Proposed AD Requirements''
paragraph, the additional P/Ns of fuel manifolds to be inspected and
replaced. GE also requested that we make clear, in the ``Summary''
paragraph, that on-wing replacement of tube (block) clamps and fuel
manifolds is based on inspection results. GE also requested that we use
alternative wording in paragraph (e) and Table 2 to paragraph (e) of
this AD.
We partially agree. We agree that we needed to clarify the P/Ns to
be removed before further flight, and those to be inspected until
removed. We changed this AD to clearly identify both groups. We also
agree that paragraph (e) of this AD required clarification. We reworded
paragraph (e) of this AD to clearly identify the requirements to
correct the unsafe condition.
Request To Allow Installation of Certain Prohibited P/Ns
Asiana Airlines, EVA Airways, Thai Airways, AIRDO, and Japan
Airlines requested that for fuel manifold, P/Ns 1303M31G12, 1303M32G12,
2420M70G01, and 2420M71G01, we reduce the inspection interval or
require non-destructive inspection at shop visits rather than require
removal and prohibit installation. The operators state that their
records do not indicate that these parts cause leaks or experience wear
that would cause their replacement, and they expressed concerns that
the reliability of the replacement fuel manifolds is lower than that of
the prohibited fuel manifolds.
We disagree. A reduced inspection interval does not prevent pigtail
cracking between shop visits. Our data does not justify a reduced
inspection interval to prevent fuel leak events, or indicate that the
new fuel manifold design has lower reliability. We did not change this
AD.
Request To Allow Use of Certain P/Ns for Drained Engine Configurations
Lufthansa Technik AG requested that we allow the use of fuel
manifold, P/Ns 2420M70G01, 2420M71G01, 1303M31G12, and 1303M32G12, as
replacement parts for drained (pre SB 73-0253) engine configurations.
The commenter states that GE's service information allows use of fuel
manifold, P/Ns 1303M31G12 and 1303M32G12, on engines with drain system
installed, and this AD does not prohibit installation of fuel manifold,
P/Ns 1303M31G10 and 1303M32G10.
We disagree. We have no data showing that drainless fuel manifolds
installed in engines with a drain system are more reliable than when
installed in engines with a drainless system. We did not change this
AD.
Request To Remove Certain Fuel Manifolds From Applicability
Lufthansa Cargo requested that we remove from the applicability of
this AD drainless fuel manifolds to which PTFE-coated para-aramid tape
was applied and the loop and tube (block) clamps were inspected.
We disagree. We received several reports of fuel leaks and a report
of under-cowl fire. The inspections alone required by this AD do not
address pigtail cracking leading to fuel leaks, and therefore do not
provide an acceptable level of safety. We did not change this AD.
Request To Remove the Word ``Uncontrolled'' From the Description of
Fire
Boeing Commercial Airplanes requested that we remove from the
preamble the word ``uncontrolled'' from the description of fire caused
by a fuel manifold leak because an uncontrolled fire in this scenario
could only occur with a significant failure of the engine nacelle fire
protection system.
We disagree. The data upon which we relied, including the Continued
Airworthiness Assessment Methodologies (CAAM) database for transport
category airplanes, includes data showing flammable fluid leaks leading
to uncontrolled fires. We did not change this AD.
[[Page 63310]]
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 editorial changes to
improve clarity. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 3139, January 17, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 3139, January 17, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD would affect 1,126 engines installed on
airplanes of U.S. registry. We also estimate that required parts cost
about $34,894 per engine. We also estimate that it will take about 6
hours to accomplish the actions required by this AD. The average labor
rate is $85 per hour. Based on these figures, we estimate the total
cost of this AD to U.S. operators to be $39,864,904.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this 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 to the extent
that it justifies making a regulatory distinction, 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:
0
a. Removing airworthiness directive (AD) 90-26-01, Amendment 39-6810
(55 FR 49611, November 30, 1990); AD 91-20-02, Amendment 39-8036 (56 FR
55231, October 25, 1991); and AD 2009-05-02, Amendment 39-15826 (74 FR
8161, February 24, 2009); and
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b. Adding the following new AD:
2014-21-01 General Electric Company: Amendment 39-17993; Docket No.
FAA-2007-28413; Directorate Identifier 2007-NE-25-AD.
(a) Effective Date
This AD is effective November 28, 2014.
(b) Affected ADs
This AD supersedes AD 90-26-01, Amendment 39-6810 (55 FR 49611,
November 30, 1990); AD 91-20-02, Amendment 39-8036 (56 FR 55231,
October 25, 1991); and AD 2009-05-02, Amendment 39-15826, (74 FR
8161, February 24, 2009).
(c) Applicability
This AD applies to all General Electric Company (GE) CF6-80C2
and CF6-80E1 series turbofan engines with fuel manifold, part number
(P/N) 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07,
1303M32G07, 1303M31G08, 1303M32G08, 1303M31G12, 1303M32G12,
2420M70G01, or 2420M71G01, installed.
(d) Unsafe Condition
This AD was prompted by a report of an under-cowl fire caused by
a fuel manifold high-pressure fuel leak, and several additional
reports of fuel leaks. We are issuing this AD to prevent failure of
the fuel manifold, which could lead to uncontrolled engine fire,
engine damage, and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Fuel Manifold Removal.
(i) After the effective date of this AD, do not return to
service any CF6-80C2 or CF6-80E1 series engine with fuel manifold P/
N 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07,
1303M32G07, 1303M31G08, or 1303M32G08, installed.
(ii) At the next engine shop visit after the effective date of
this AD, remove from service fuel manifold P/Ns 1303M31G12,
1303M32G12, 2420M70G01, and 2420M71G01.
(2) Fuel Manifold, Loop Clamp, and Tube (Block) Clamp Initial
and Repetitive Inspection and Replacement.
(i) For CF6-80C2 and CF680E1 series engines, with fuel manifold,
P/N 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01 installed,
inspect the fuel manifold and replace if required by inspection
results, and replace the loop clamps as follows:
(A) For CF6-80C2 series engines, use paragraphs 3.A, 3.C, and
3.D of GE CF6-80C2 Service Bulletin (SB) No. S/B 73-0326 R04,
Revision 4, dated December 23, 2009, to do the inspection and
replacements.
(B) For CF6-80E1 series engines, use paragraphs 3.A, 3.B, and
3.C of GE CF6-80E1 SB No. S/B 73-0061 R04, Revision 4, dated
December 23, 2009, to do the inspection and replacements.
(C) Compliance time for fuel manifold inspection and loop clamp
replacement:
(1) If the engine is a first-run engine, inspect the fuel
manifold and replace the loop clamps within 7,500 flight hours (FH)
time-since-new (TSN).
(2) If the engine's fuel manifold was ever inspected and new
loop clamps were previously installed, inspect the fuel manifold and
replace the loop clamps within 7,500 FH time-since-last-inspection
(TSLI).
(3) If the engine's fuel manifold was not inspected, new loop
clamps were not installed, or it is unknown when the loop clamps
were installed, inspect the fuel manifold and replace the loop
clamps within 1,750 FH time-since-last-shop-visit or within 4 months
after the effective date of this AD, whichever occurs later.
(ii) For CF6-80C2 and CF6-80E1 series engines, with fuel
manifold, P/N 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01,
with tube (block) clamp, P/N 1153M26G15, installed, inspect fuel
manifold and tube (block) clamps, and replace if required by
inspection results, as follows:
(A) For CF6-80C2 series engines, use paragraphs 3.A.(1) through
3.A.(8) and 3.C.(1) through 3.C.(2) of GE CF6-80C2 SB No. S/B 73-
0414, Revision 1, dated May 29, 2014, to do the inspection.
(B) For CF6-80E1 series engines, use paragraphs 3.A.(1) through
3.A.(6) and 3.C.(1)
[[Page 63311]]
through 3.C.(2) of GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated
May 29, 2014, to do the inspection.
(C) Compliance time for fuel manifold and tube (block) clamp
inspection:
(1) If the engine is a first-run engine, inspect the fuel
manifold and tube (block) clamps within 7,500 FH TSN or within 3
months after the effective date of this AD, whichever occurs later.
(2) If the engine was previously inspected using either of GE
CF6-80C2 SB No. S/B 73-0414, Revision 1, dated May 29, 2014, or GE
CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29, 2014, or
earlier versions, then inspect the fuel manifold and tube (block)
clamps within 7,500 FH TSLI or within 3 months after the effective
date of this AD, whichever occurs later.
(3) If the engine is not a first-run engine and was not
previously inspected using GE CF6-80C2 SB No. S/B 73-0414, Revision
1, dated May 29, 2014, or GE CF6-80E1 SB No. S/B 73-0121, Revision
1, dated May 29, 2014, or earlier versions, then inspect the fuel
manifold and tube (block) clamps within 7,500 FH TSN or within 3
months after the effective date of this AD, whichever occurs later.
(iii) Thereafter, inspect fuel manifold, P/Ns 1303M31G12,
1303M32G12, 2420M70G01, and 2420M71G01, and tube (block) clamps,
replace if required by inspection results, and replace the loop
clamps within every 7,500 FH TSLI, using paragraphs (e)(2)(i)(A),
(e)(2)(i)(B), (e)(2)(ii)(A), and (e)(2)(ii)(B) of this AD, as
applicable.
(f) Definition
(1) For the purposes of this AD, an engine shop visit is the
induction of an engine into the shop where the separation of a major
engine flange occurs, except that induction into the shop for any of
the reasons in paragraphs (f)(i) through (f)(iv) of this AD is not
an engine shop visit:
(i) Induction of an engine into a shop solely for removal of the
compressor top or bottom case for airfoil maintenance, or for
variable stator vane bushing replacement;
(ii) Induction of an engine into a shop solely for replacement
of the turbine rear frame;
(iii) Induction of an engine into a shop solely for replacement
of the accessory gearbox or transfer gearbox, or both; or
(iv) Induction of an engine into a shop solely for core
vibration trim balance procedure that requires separation of a major
engine flange.
(2) For the purposes of this AD, a first-run engine is an engine
that has not had a shop visit since entering service.
(g) Alternative Methods of Compliance (AMOCs)
(1) 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.
(2) Previously approved AMOCs for AD 2009-05-02 (74 FR 8161,
February 24, 2009) remain approved for the corresponding
requirements of paragraphs (e)(1) and (e)(2) of this AD.
(h) Related Information
(1) For more information about this AD, contact Kasra Sharifi,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. 01803; phone (781) 238-7773; fax: (781) 238-7199; email:
kasra.sharifi@faa.gov.
(2) For additional details of the under cowl fire that prompted
this AD, refer to National Transportation Safety Board (NTSB) safety
recommendation (SR) A-13-028. The NTSB SR is available on the
Internet at https://www.ntsb.gov/doclib/recletters/2013/A-13-028.pdf.
(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) General Electric Company (GE) CF6-80C2 Service Bulletin (SB)
No. 73-0326 R04, Revision 4, dated December 23, 2009.
(ii) GE CF6-80C2 SB No. S/B 73-0414, Revision 1, dated May 29,
2014.
(iii) GE CF6-80E1 SB No. 73-0061 R04, Revision 4, dated December
23, 2009.
(iv) GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29,
2014.
(3) For GE service information identified in this AD, contact
General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552-3272; email: geae.aoc@ge.com.
(4) You may view this service information at the FAA, Engine &
Propeller Directorate, 12 New England Executive Park, 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/ibr-locations.html.
Issued in Burlington, Massachusetts, on October 7, 2014.
Kim Smith,
Acting Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-24697 Filed 10-22-14; 8:45 am]
BILLING CODE 4910-13-P
