Airworthiness Directives; General Electric Company Turbofan Engines, 47534-47537 [2013-18840]
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47534
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
TABLE 1 TO PARAGRAPH (e)—Continued
UT inspect grip, P/N
tkelley on DSK3SPTVN1PROD with RULES
204–011–121–005 or –113, if the grip was EVER installed on a Model 205B or Model
UH–1N helicopter .........................................................................................................
204–011–121–117, if the grip was EVER installed on a Model 205B helicopter ...........
(3) At intervals not to exceed 1,200 hours
TIS or 24 months, whichever occurs first:
(i) Remove each main rotor blade, and
(ii) Inspect each grip buffer pad on the
inner surfaces of each grip tang for
delamination as depicted in Figure 5–7,
Inspection of Main Rotor Hub Grip (1200
Hours), Revision 9, dated August 8, 2008, of
Chapter 5, Inspections and Component
Overhaul Schedule, Revision 11, dated April
30, 2010, of Bell Helicopter Textron, Inc.,
BHT–212–MM–1, Revision 13, dated
September 16, 2010. If there is any
delamination, remove the buffer pad and
inspect the grip surface for corrosion or other
damage.
(4) Within 2,400 hours TIS or at the next
overhaul of the main rotor hub, whichever
occurs first, and then at intervals not to
exceed 2,400 hours TIS:
(i) Remove each main rotor blade.
(ii) Remove each grip buffer pad (if
installed) from the inner surfaces of each grip
tang.
(iii) Visually inspect the grip surfaces for
corrosion or other damage.
(iv) Fluorescent-penetrant inspect (FPI) the
grip for a crack, paying particular attention
to the upper and lower grip tangs. When
inspecting a grip, P/N 204–011–121–005,
204–011–121–009, or 204–011–121–113, or
ASI–4011–121–9, pay particular attention to
the leading and trailing edges of the grip
barrel.
(5) Before further flight:
(i) Replace any cracked grip with an
airworthy grip.
(ii) Replace any grip with any corrosion or
other damage with an airworthy grip, or
repair the grip if the corrosion or other
damage is within the maximum repair
limitations.
(iii) Remove any grip, P/N 204–011–121–
009 or ASI–4011–121–9, that has been in
service for 15,000 or more hours TIS.
(iv) Remove any grip, P/N 204–011–121–
121, that has been in service for 25,000 or
more hours TIS.
(6) Revise the Airworthiness Limitations
section of the applicable maintenance
manual or the Instructions for Continued
Airworthiness (ICA) by establishing a new
retirement life of 15,000 hours TIS for grip,
P/N 204–011–121–009 or ASI–4011–121–9,
and 25,000 hours TIS for grip, P/N 204–011–
121–121, by marking pen and ink changes or
inserting a copy of this AD into the
maintenance manual or ICA.
(7) Record a 15,000 hour TIS life limit for
each grip, P/N 204–011–121–009 or ASI–
4011–121–9, and a 25,000 hour life limit for
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17:14 Aug 05, 2013
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each grip, P/N 204–011–121–121, on the
applicable component history card or
equivalent record.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5170;
email 7-avs-asw-170@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
BHTI Alert Service Bulletin (ASB) 212–94–
92, Revision A, dated March 13, 1995; BHTI
Operations Safety Notice (OSN) 204–85–6,
OSN 205–85–9, and OSN 212–85–13, all
dated November 14, 1985 and co-published
as one document; BHTI ASB 205B–02–39,
Revision B, dated November 22, 2002; and
BHTI ASB 212–02–116, Revision A, dated
October 30, 2002, which are not incorporated
by reference, contain additional information
about the subject of this AD.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6220, Main rotor head.
(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) Bell Helicopter Textron, Inc.
Nondestructive Inspection Procedure, Log
No. 00–340, Revision E, dated April 9, 2002.
(ii) Figure 5–7, Inspection of Main Rotor
Hub Grip (1200 Hours), Revision 9, dated
August 8, 2008, of Chapter 5, Inspections and
Component Overhaul Schedule, Revision 11,
dated April 30, 2010, of Bell Helicopter
Textron, Inc., BHT–212–MM–1, Revision 13,
dated September 16, 2010.
(3) For BHTI service information identified
in this AD, contact Bell Helicopter Textron,
PO 00000
Thereafter, at intervals not to exceed the following number of hours
TIS or the engine start/stop cycles,
whichever occurs first:
Within 30 days,
for a grip with
the following or
more hours TIS:
Frm 00008
Fmt 4700
Sfmt 4700
Hours TIS
4,000
500
Engine start/stop
cycles
400
150
1,600
600
Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280–3391; fax (817) 280–
6466; or at https://www.bellcustomer.com/
files/.
(4) You may review a copy of this service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(5) You may also review a copy of 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 Fort Worth, Texas, on June 18,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–18570 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0447; Directorate
Identifier 2013–NE–17–AD; Amendment 39–
17536; AD 2013–15–20]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
emergency airworthiness directive (AD)
2013–14–51 for General Electric
Company (GE) GE90–110B1 and GE90–
115B turbofan engines with affected
transfer gearbox assembly (TGB) radial
gearshafts installed. AD 2013–14–51
was sent previously to all known U.S.
owners and operators of GE90–110B1
and GE90–115B turbofan engines. AD
2013–14–51 prohibited operation of an
airplane if more than one installed
engine has an affected TGB radial
SUMMARY:
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
tkelley on DSK3SPTVN1PROD with RULES
gearshaft. This AD contains the same
prohibition as AD 2013–14–51 and also
prohibits operation of any airplane 60
days after the effective date of this new
AD if any installed engine has an
affected TGB radial gearshaft. This new
AD also revises the applicability by
adding GE90–76B, GE90–77B, GE90–
85B, GE90–90B, GE90–94B, and GE90–
113B turbofan engine models and adds
a mandatory terminating action. This
new AD was prompted by reports of
three failures of TGB radial gearshafts
which resulted in in-flight shutdowns
(IFSDs). We are issuing this new AD to
prevent failure of the TGB radial
gearshaft, which could result in IFSD of
one or more engines, loss of thrust
control, and damage to the airplane.
DATES: This AD is effective August 21,
2013.
We must receive any comments on
this AD by September 20, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact General Electric
Company, One Neumann Way, Room
285, Cincinnati, OH; 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://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Carlos Fernandes, Aerospace Engineer,
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17:14 Aug 05, 2013
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Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7189; fax: 781–238–
7199; email: carlos.fernandes@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 16, 2013, we issued
emergency AD 2013–10–52 (issued on
June 16, 2013, as a Final Rule, Request
for Comments (78 FR 38195, June 26,
2013)), which was immediately effective
to owners and operators of GE GE90–
110B1 and GE90–115B turbofan
engines. That AD resulted from reports
of two failures of TGB radial gearshafts
that resulted in IFSDs. That AD
prohibited operation of an airplane with
affected TGBs installed on both engines.
On July 12, 2013, we issued
emergency AD 2013–14–51, superseding
AD 2013–10–52 (78 FR 38195, June 26,
2013). AD 2013–14–51 also prohibits
operation of an airplane with affected
TGB radial gearshafts installed on both
engines. AD 2013–14–51 resulted from
a report of an additional failure of a TGB
radial gearshaft, outside the population
identified in AD 2013–10–52. We issued
ADs 2013–10–52 and 2013–14–51 to
prevent failure and separation of the
TGB radial gearshaft, which could result
in IFSD of one or more engines, loss of
thrust control, and damage to the
airplane.
Actions Since AD 2013–14–51 Was
Issued
Since we issued emergency AD 2013–
14–51, dated July 12, 2013, we
determined that airplanes with an
installed engine with an affected TGB
radial gearshaft should not be allowed
to operate more than 60 days after the
effective date of this new AD. We also
revised the Applicability of this new AD
since we determined that the affected
TGB radial gearshafts are installed on
additional GE90 engine models besides
the GE90–110B1 and GE90–115B. We
also determined the need to add a
mandatory terminating action.
Relevant Service Information
We reviewed GE GE90–100 Series
Alert Service Bulletin (ASB) No. GE90–
100 S/B 72–A0568, dated July 10, 2013;
GE GE90–100 Series Service Bulletin
(SB) No. GE90–100 S/B 72–0569,
Revision 0, dated July 19, 2013; and GE
GE90 SB No. GE90 S/B 72–1091,
Revision 0, dated June 11, 2013, which
provide additional information
regarding the affected TGB radial
gearshafts. We also reviewed GE GE90–
100 Series SB No. GE90–100 S/B 72–
0563, Revision 0, dated June 21, 2013,
and Revision 1, dated July 10, 2013; and
PO 00000
Frm 00009
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Sfmt 4700
47535
GE GE90 SB No. GE90 S/B 72–1066,
Revision 0, dated June 21, 2013; which
provide information regarding the
mandatory terminating action.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
AD Requirements
This AD prohibits operation of an
airplane with affected TGB radial
gearshafts installed on both engines
after the effective date of this AD. This
AD also prohibits operation of an
airplane with affected TGB radial
gearshafts installed on any engine 60
days after the effective date of this AD.
This AD also adds a mandatory
terminating action, namely, to install a
TGB radial gearshaft that is eligible for
installation.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because of the before further flight
compliance time. Therefore, we find
that notice and opportunity for prior
public comment are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2013–0447 and directorate
identifier 2013–NE–17–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
Regulatory Findings
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD will affect
about 16 GE90 engines installed on
airplanes of U.S. registry. We also
estimate that it will take about eight
hours per engine to replace the TGB
radial gearshaft. The average labor rate
is $85 per hour. The cost of this part is
about $16,700. Based on these figures,
we estimate the total cost of this AD to
U.S. operators to be $278,080.
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.
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 part 39 of the Federal
Aviation Regulations (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:
a. Removing AD 2013–10–52 (78 FR
38195, June 26, 2013); and
■ b. Adding the following new AD:
2013–15–20: Amendment 39–17536;
Docket No. FAA–2013–0447; Directorate
Identifier 2013–NE–17–AD.
■
■
(a) Effective Date
This AD is effective August 21, 2013.
(b) Affected ADs
This AD supersedes Emergency AD
2013–14–51, Directorate ID 2013–NE–
17–AD, dated July 12, 2013. This AD
also removes AD 2013–10–52 (78 FR
38195, June 26, 2013) from the Code of
Federal Regulations.
(c) Applicability
General Electric Company (GE) GE90–
76B, GE90–77B, GE90–85B, GE90–90B,
GE90–94B, GE90–110B1, GE90–113B
and GE90–115B turbofan engines with a
transfer gearbox assembly (TGB) radial
gearshaft, part number (P/N)
1995M24P02, serial number (S/N) listed
in Figure 1 to paragraph (c) of this AD,
installed.
tkelley on DSK3SPTVN1PROD with RULES
FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’ S
FIA0KCYG
FIA0K63F
FIA0K3A3
FIA0JVRE
FIA0H0VM
FIA0K3A4
FIA0K62T
FIA0JJ53
FIA0K89W
FIA0KCW8
FIA0K3A6
FIA0HY8C
FIA0K3AP
FIA0J7WG
FIA0JVRL
FIA0J7V1
FIA0JVRM
FIA0K3AV
FIA0J7V8
FIA0J7WE
FIA0K3A2
FIA0K3A1
FIA0K3AN
FIA0JVRP
FIA0JJ6F
FIA0JJ6J
FIA0JVRV
FIA0H0VL
FIA0K89T
FIA0K89Y
VerDate Mar<15>2010
FIA0JETA
FIA0J7V2
FIA0KCYM
FIA0JJ6E
FIA0JNJH
FIA0K62W
FIA0K89P
FIA0JJ57
FIA0JJ56
FIA0KH9Y
FIA0KCYP
FIA0JJ55
FIA0KH9G
FIA0KH9H
FIA0KH9K
FIA0KH9C
FIA0K63H
FIA0K63M
FIA0K62Y
FIA0JVP9
FIA0K63E
FIA0K3AY
FIA0JVRT
FIA0HY8E
FIA0HY8N
FIA0J7V0
FIA0J7V3
FIA0J7V5
FIA0HY8H
FIA0HEG2
17:14 Aug 05, 2013
Jkt 229001
PO 00000
FIA0H0VJ FIA0HL0C
FIA0K62R
FIA0K63C
FIA0K89H
FIA0KCYK
FIA0K3A5
FIA0HWKA
FIA0KCYR
FIA0HWKE
FIA0J7WH
FIA0JER9
FIA0JNJJ
FIA0JVRR
FIA0JNJM
FIA0KH9R
FIA0KH9P
FIA0K89C FIA0HY8F
FIA0JVRH
FIA0K89L
FIA0JER6
FIA0JETH
FIA0H0VC
FIA0K3AL
FIA0J7VV
FIA0J7VP
FIA0J7V9 FIA0JETF
FIA0HWJ8
FIA0H0VA
FIA0KCYL
FIA0HY79
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FIA0HLY9
FIA0HL0E
FIA0HL0F
FIA0HL0G
FIA0HLY7
FIA0HJTE
FIA0HJTJ
FIA0HJTG
FIA0HJTC
FIA0HJTF
FIA0HJTH
FIA0HJTA
FIA0HJR9
FIA0HWJ7
FIA0HY76
FIA0H0VK
FIA0J7VR
FIA0JJ58
FIA0JJ6C
FIA0JNJF
FIA0JNJK
FIA0JVRC
FIA0J7V4
FIA0HEG4
FIA0HWJ9
FIA0HWJ5
FIA0HWJ6
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
47537
FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’ S—Continued
FIA0JETL
FIA0JER8
FIA0J7WC
FIA0JETE
FIA0K3AT
FIA0JJ59
FIA0K3AW
FIA0JVRN
FIA0JNH8
FIA0JETN
FIA0HY78
FIA0HY75
FIA0HEG0
FIA0KH9E
FIA0KH9F
FIA0H0T9
FIA0HLY3
FIA0K62V
FIA0HEGY
FIA0HWKC
FIA0K3A0
FIA0JVRJ
FIA0K8AA
FIA0KCYT
FIA0KH9T FIA0KH9W
FIA0HEG1
FIA0HEG3
FIA0J7WJ
FIA0JER7
FIA0JVRF
FIA0K63K
FIA0J7WK
FIA0JER5
FIA0JETM
(d) Unsafe Condition
This AD was prompted by reports of
three failures of TGB radial gearshafts
which resulted in in-flight shutdowns
(IFSDs). We are issuing this AD to
prevent failure of the TGB radial
gearshaft, which could result in IFSD of
one or more engines, loss of thrust
control, and damage to the airplane.
(e) Compliance
(1) Comply with this AD within the
compliance times specified, unless
already done.
(2) Before further flight after the
effective date of this AD, do not operate
the airplane if more than one installed
engine has a TGB radial gearshaft P/N
and S/N listed in Figure 1 to paragraph
(c) of this AD.
(f) Mandatory Terminating Action
No later than 60 days after the
effective date of this AD, as terminating
action to the requirements of paragraph
(e) of this AD, replace all TGB radial
gearshafts identified in Figure 1 to
paragraph (c) of this AD that are
installed on an airplane with TGB radial
gearshafts that are eligible for
installation.
(g) Prohibition on Operation
Sixty days after the effective date of
this AD, do not operate any airplane
that has an engine installed that has a
TGB radial gearshaft P/N and S/N listed
in Figure 1 to paragraph (c) of this AD.
tkelley on DSK3SPTVN1PROD with RULES
(h) Definition
For the purposes of this AD, a TGB
radial gearshaft eligible for installation
is:
(1) A TGB radial gearshaft P/N and S/
N, not listed in this AD or
(2) A TGB radial gearshaft with an S/
N listed in paragraph (c) of this AD with
part number 1995M24P04, 2205M61P01
or 2205M61P02.
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
FIA0KH9J
FIA0HY8G
FIA0HY8M
FIA0HY8A
FIA0H0VG
FIA0K3AR
FIA0JETC
FIA0JNJC
FIA0K63L
FIA0KCYN
FIA0JVRG
FIA0HY8L
FIA0HY8J
FIA0H0VH FIA0HLY1
FIA0H0VF
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification
Office, FAA, may approve AMOCs for
this AD. Use the procedures in 14 CFR
39.19 to make your request.
(j) Related Information
(k) Material Incorporated by Reference
None.
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Issued in Burlington, Massachusetts, on
July 25, 2013.
Frank P. Paskiewicz,
Acting Director, Aircraft Certification Service.
[FR Doc. 2013–18840 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
(1) For more information about this
AD, contact Carlos Fernandes,
Aerospace Engineer, Engine
Certification Office, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7189; fax: 781–
238–7199; email:
carlos.fernandes@faa.gov.
(2) GE GE90–100 Series Alert Service
Bulletin No. GE90–100 S/B 72–A0568,
Revision 0, dated July 10, 2013; GE
GE90–100 Series Service Bulletin (SB)
No. GE90–100 S/B 72–0569, Revision 0,
dated July 19, 2013; GE GE90–100
Series SB No. GE90–100 S/B 72–0563,
Revision 0, dated June 21, 2013, and
Revision 1, dated July 10, 2013; GE
GE90 SB No. GE90 S/B 72–1066,
Revision 0, dated June 21, 2013; and GE
GE90 SB No. GE90 S/B 72–1091,
Revision 0, dated June 11, 2013, can be
obtained from GE using the contact
information in paragraph (j)(3) of this
AD.
(3) For service information identified
in this AD, contact General Electric
Company, One Neumann Way, Room
285, Cincinnati, OH; 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.
PO 00000
FIA0J7VW
FIA0J7VY
FIA0J7VT
FIA0J7WF
FIA0J7V6
FIA0K89G
FIA0K89K
FIA0K89R
FIA0KCYJ
FIA0JJ6G
FIA0JJ6A
FIA0HY8K
FIA0HLY6
FIA0HLY0
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1033; Directorate
Identifier 2010–NM–266–AD; Amendment
39–17504; AD 2013–13–16]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2005–07–
04 for all Airbus Model A330–200 and
–300 series airplanes, and Model A340–
200 and –300 series airplanes. AD 2005–
07–04 required repetitive inspections to
detect discrepancies of the transfer
tubes and the collar of the ball nut of the
trimmable horizontal stabilizer actuator
(THSA), and corrective action if
necessary; repetitive inspections for
discrepancies of the ball screw
assembly, and corrective action if
necessary; repetitive greasing of the
THSA ball nut, and replacement of the
THSA if necessary; and modification or
replacement (as applicable) of the ball
nut assembly, which ends certain
repetitive inspections. This new AD
removes certain inspections, revises
certain actions, and adds airplanes to
the applicability. This AD was
prompted by several reports of
SUMMARY:
E:\FR\FM\06AUR1.SGM
06AUR1
]]>Agencies
[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47534-47537]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18840]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0447; Directorate Identifier 2013-NE-17-AD;
Amendment 39-17536; AD 2013-15-20]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding emergency airworthiness directive (AD)
2013-14-51 for General Electric Company (GE) GE90-110B1 and GE90-115B
turbofan engines with affected transfer gearbox assembly (TGB) radial
gearshafts installed. AD 2013-14-51 was sent previously to all known
U.S. owners and operators of GE90-110B1 and GE90-115B turbofan engines.
AD 2013-14-51 prohibited operation of an airplane if more than one
installed engine has an affected TGB radial
[[Page 47535]]
gearshaft. This AD contains the same prohibition as AD 2013-14-51 and
also prohibits operation of any airplane 60 days after the effective
date of this new AD if any installed engine has an affected TGB radial
gearshaft. This new AD also revises the applicability by adding GE90-
76B, GE90-77B, GE90-85B, GE90-90B, GE90-94B, and GE90-113B turbofan
engine models and adds a mandatory terminating action. This new AD was
prompted by reports of three failures of TGB radial gearshafts which
resulted in in-flight shutdowns (IFSDs). We are issuing this new AD to
prevent failure of the TGB radial gearshaft, which could result in IFSD
of one or more engines, loss of thrust control, and damage to the
airplane.
DATES: This AD is effective August 21, 2013.
We must receive any comments on this AD by September 20, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact General
Electric Company, One Neumann Way, Room 285, Cincinnati, OH; 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://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7189;
fax: 781-238-7199; email: carlos.fernandes@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 16, 2013, we issued emergency AD 2013-10-52 (issued on June
16, 2013, as a Final Rule, Request for Comments (78 FR 38195, June 26,
2013)), which was immediately effective to owners and operators of GE
GE90-110B1 and GE90-115B turbofan engines. That AD resulted from
reports of two failures of TGB radial gearshafts that resulted in
IFSDs. That AD prohibited operation of an airplane with affected TGBs
installed on both engines.
On July 12, 2013, we issued emergency AD 2013-14-51, superseding AD
2013-10-52 (78 FR 38195, June 26, 2013). AD 2013-14-51 also prohibits
operation of an airplane with affected TGB radial gearshafts installed
on both engines. AD 2013-14-51 resulted from a report of an additional
failure of a TGB radial gearshaft, outside the population identified in
AD 2013-10-52. We issued ADs 2013-10-52 and 2013-14-51 to prevent
failure and separation of the TGB radial gearshaft, which could result
in IFSD of one or more engines, loss of thrust control, and damage to
the airplane.
Actions Since AD 2013-14-51 Was Issued
Since we issued emergency AD 2013-14-51, dated July 12, 2013, we
determined that airplanes with an installed engine with an affected TGB
radial gearshaft should not be allowed to operate more than 60 days
after the effective date of this new AD. We also revised the
Applicability of this new AD since we determined that the affected TGB
radial gearshafts are installed on additional GE90 engine models
besides the GE90-110B1 and GE90-115B. We also determined the need to
add a mandatory terminating action.
Relevant Service Information
We reviewed GE GE90-100 Series Alert Service Bulletin (ASB) No.
GE90-100 S/B 72-A0568, dated July 10, 2013; GE GE90-100 Series Service
Bulletin (SB) No. GE90-100 S/B 72-0569, Revision 0, dated July 19,
2013; and GE GE90 SB No. GE90 S/B 72-1091, Revision 0, dated June 11,
2013, which provide additional information regarding the affected TGB
radial gearshafts. We also reviewed GE GE90-100 Series SB No. GE90-100
S/B 72-0563, Revision 0, dated June 21, 2013, and Revision 1, dated
July 10, 2013; and GE GE90 SB No. GE90 S/B 72-1066, Revision 0, dated
June 21, 2013; which provide information regarding the mandatory
terminating action.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD prohibits operation of an airplane with affected TGB radial
gearshafts installed on both engines after the effective date of this
AD. This AD also prohibits operation of an airplane with affected TGB
radial gearshafts installed on any engine 60 days after the effective
date of this AD. This AD also adds a mandatory terminating action,
namely, to install a TGB radial gearshaft that is eligible for
installation.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because of
the before further flight compliance time. Therefore, we find that
notice and opportunity for prior public comment are impracticable and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2013-0447 and directorate identifier 2013-NE-17-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each
[[Page 47536]]
substantive verbal contact we receive about this AD.
Costs of Compliance
We estimate that this AD will affect about 16 GE90 engines
installed on airplanes of U.S. registry. We also estimate that it will
take about eight hours per engine to replace the TGB radial gearshaft.
The average labor rate is $85 per hour. The cost of this part is about
$16,700. Based on these figures, we estimate the total cost of this AD
to U.S. operators to be $278,080.
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 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 part 39 of the Federal Aviation
Regulations (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 AD 2013-10-52 (78 FR 38195, June 26, 2013); and
0
b. Adding the following new AD: 2013-15-20: Amendment 39-17536; Docket
No. FAA-2013-0447; Directorate Identifier 2013-NE-17-AD.
(a) Effective Date
This AD is effective August 21, 2013.
(b) Affected ADs
This AD supersedes Emergency AD 2013-14-51, Directorate ID 2013-NE-
17-AD, dated July 12, 2013. This AD also removes AD 2013-10-52 (78 FR
38195, June 26, 2013) from the Code of Federal Regulations.
(c) Applicability
General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-
90B, GE90-94B, GE90-110B1, GE90-113B and GE90-115B turbofan engines
with a transfer gearbox assembly (TGB) radial gearshaft, part number
(P/N) 1995M24P02, serial number (S/N) listed in Figure 1 to paragraph
(c) of this AD, installed.
Figure 1 to Paragraph (c)--TGB Radial Gearshaft P/N 1995M24P02 S/N's
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
FIA0KCYG FIA0JETA FIA0H0VJ FIA0HL0C
FIA0K63F FIA0J7V2 FIA0K62R FIA0HLY9
FIA0K3A3 FIA0KCYM FIA0K63C FIA0HL0E
FIA0JVRE FIA0JJ6E FIA0K89H FIA0HL0F
FIA0H0VM FIA0JNJH FIA0KCYK FIA0HL0G
FIA0K3A4 FIA0K62W FIA0K3A5 FIA0HLY7
FIA0K62T FIA0K89P FIA0HWKA FIA0HJTE
FIA0JJ53 FIA0JJ57 FIA0KCYR FIA0HJTJ
FIA0K89W FIA0JJ56 FIA0HWKE FIA0HJTG
FIA0KCW8 FIA0KH9Y FIA0J7WH FIA0HJTC
FIA0K3A6 FIA0KCYP FIA0JER9 FIA0HJTF
FIA0HY8C FIA0JJ55 FIA0JNJJ FIA0HJTH
FIA0K3AP FIA0KH9G FIA0JVRR FIA0HJTA
FIA0J7WG FIA0KH9H FIA0JNJM FIA0HJR9
FIA0JVRL FIA0KH9K FIA0KH9R FIA0HWJ7
FIA0J7V1 FIA0KH9C FIA0KH9P FIA0HY76
FIA0JVRM FIA0K63H FIA0K89C FIA0HY8F
FIA0K3AV FIA0K63M FIA0JVRH FIA0H0VK
FIA0J7V8 FIA0K62Y FIA0K89L FIA0J7VR
FIA0J7WE FIA0JVP9 FIA0JER6 FIA0JJ58
FIA0K3A2 FIA0K63E FIA0JETH FIA0JJ6C
FIA0K3A1 FIA0K3AY FIA0H0VC FIA0JNJF
FIA0K3AN FIA0JVRT FIA0K3AL FIA0JNJK
FIA0JVRP FIA0HY8E FIA0J7VV FIA0JVRC
FIA0JJ6F FIA0HY8N FIA0J7VP FIA0J7V4
FIA0JJ6J FIA0J7V0 FIA0J7V9 FIA0JETF
FIA0JVRV FIA0J7V3 FIA0HWJ8 FIA0HEG4
FIA0H0VL FIA0J7V5 FIA0H0VA FIA0HWJ9
FIA0K89T FIA0HY8H FIA0KCYL FIA0HWJ5
FIA0K89Y FIA0HEG2 FIA0HY79 FIA0HWJ6
[[Page 47537]]
FIA0JETL FIA0K62V FIA0KH9J FIA0J7VW
FIA0JER8 FIA0HEGY FIA0HY8G FIA0J7VY
FIA0J7WC FIA0HWKC FIA0HY8M FIA0J7VT
FIA0JETE FIA0K3A0 FIA0HY8A FIA0J7WF
FIA0K3AT FIA0JVRJ FIA0H0VG FIA0J7V6
FIA0JJ59 FIA0K8AA FIA0K3AR FIA0K89G
FIA0K3AW FIA0KCYT FIA0JETC FIA0K89K
FIA0JVRN FIA0KH9T FIA0KH9W FIA0K89R
FIA0JNH8 FIA0HEG1 FIA0JNJC FIA0KCYJ
FIA0JETN FIA0HEG3 FIA0K63L FIA0JJ6G
FIA0HY78 FIA0J7WJ FIA0KCYN FIA0JJ6A
FIA0HY75 FIA0JER7 FIA0JVRG FIA0HY8K
FIA0HEG0 FIA0JVRF FIA0HY8L FIA0HLY6
FIA0KH9E FIA0K63K FIA0HY8J FIA0HLY0
FIA0KH9F FIA0J7WK FIA0H0VH FIA0HLY1
FIA0H0T9 FIA0JER5 FIA0H0VF FIA0HLY4
FIA0HLY3 FIA0JETM
----------------------------------------------------------------------------------------------------------------
(d) Unsafe Condition
This AD was prompted by reports of three failures of TGB radial
gearshafts which resulted in in-flight shutdowns (IFSDs). We are
issuing this AD to prevent failure of the TGB radial gearshaft, which
could result in IFSD of one or more engines, loss of thrust control,
and damage to the airplane.
(e) Compliance
(1) Comply with this AD within the compliance times specified,
unless already done.
(2) Before further flight after the effective date of this AD, do
not operate the airplane if more than one installed engine has a TGB
radial gearshaft P/N and S/N listed in Figure 1 to paragraph (c) of
this AD.
(f) Mandatory Terminating Action
No later than 60 days after the effective date of this AD, as
terminating action to the requirements of paragraph (e) of this AD,
replace all TGB radial gearshafts identified in Figure 1 to paragraph
(c) of this AD that are installed on an airplane with TGB radial
gearshafts that are eligible for installation.
(g) Prohibition on Operation
Sixty days after the effective date of this AD, do not operate any
airplane that has an engine installed that has a TGB radial gearshaft
P/N and S/N listed in Figure 1 to paragraph (c) of this AD.
(h) Definition
For the purposes of this AD, a TGB radial gearshaft eligible for
installation is:
(1) A TGB radial gearshaft P/N and S/N, not listed in this AD or
(2) A TGB radial gearshaft with an S/N listed in paragraph (c) of
this AD with part number 1995M24P04, 2205M61P01 or 2205M61P02.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures in 14 CFR 39.19 to make your request.
(j) Related Information
(1) For more information about this AD, contact Carlos Fernandes,
Aerospace Engineer, Engine Certification Office, FAA, 12 New England
Executive Park, Burlington, MA 01803; phone: 781-238-7189; fax: 781-
238-7199; email: carlos.fernandes@faa.gov.
(2) GE GE90-100 Series Alert Service Bulletin No. GE90-100 S/B 72-
A0568, Revision 0, dated July 10, 2013; GE GE90-100 Series Service
Bulletin (SB) No. GE90-100 S/B 72-0569, Revision 0, dated July 19,
2013; GE GE90-100 Series SB No. GE90-100 S/B 72-0563, Revision 0, dated
June 21, 2013, and Revision 1, dated July 10, 2013; GE GE90 SB No. GE90
S/B 72-1066, Revision 0, dated June 21, 2013; and GE GE90 SB No. GE90
S/B 72-1091, Revision 0, dated June 11, 2013, can be obtained from GE
using the contact information in paragraph (j)(3) of this AD.
(3) For service information identified in this AD, contact General
Electric Company, One Neumann Way, Room 285, Cincinnati, OH; 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.
(k) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on July 25, 2013.
Frank P. Paskiewicz,
Acting Director, Aircraft Certification Service.
[FR Doc. 2013-18840 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P
