Airworthiness Directives; International Aero Engines AG V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 Turbofan Engines, 59067-59071 [2010-23832]
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations
FAA–2007–28077; Directorate Identifier
2007–NE–20–AD.
Optional Terminating Action
DEPARTMENT OF TRANSPORTATION
(a) This airworthiness directive (AD)
becomes effective November 1, 2010.
(f) Incorporating modification TU166
terminates the repetitive inspection
requirements of paragraphs (e)(2)(i) and
(e)(2)(ii) of this AD.
Affected ADs
FAA AD Differences
(b) This AD revises AD 2009–09–03,
Amendment 39–15889.
´
(c) This AD applies to Turbomeca S.A.
ARRIEL 2B and 2B1 turboshaft engines that
don’t incorporate modification TU166. These
engines are installed on, but not limited to,
Eurocopter AS 350 B3 and EC 130 B4
helicopters.
(g) For clarification, we restructured the
actions and compliance wording of this AD.
´
(h) We deleted the Turbomeca reporting
requirement from the AD.
(i) Although EASA Airworthiness Directive
2007–0109R1, dated November 9, 2009,
applies to the ARRIEL 2B1A engine, this AD
does not apply to that model because it has
no U.S. type certificate.
Reason
Alternative Methods of Compliance
(AMOCs)
Effective Date
Applicability
(d) This AD results from:
Since issuance of AD 2007–0109,
´
Turbomeca has released modification TU166
which consists in inserting HP blade
dampers between the HP disc and the HP
blade platform. Introduction of these
dampers has demonstrated to limit axial
displacement of the HP blade relative to the
disk in case of blade lock rupture or opening,
therefore eliminating the need for inspection
and replacement.
We are issuing this AD to prevent an
uncommanded in-flight engine shutdown
which could result in an emergency
autorotation landing or an accident.
Actions and Compliance
(e) Unless already done, do the following
actions:
Initial Inspection
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(1) Perform an initial high-pressure (HP)
turbine borescope inspection according to
´
Turbomeca S.A. Mandatory Service Bulletin
(MSB) No. 292 72 2825, Version B, dated
September 21, 2009, or earlier version as
follows:
(i) For engines with fewer than 500 hours
and 450 cycles since new or since the last HP
turbine borescope inspection, inspect before
reaching 600 hours or 500 cycles whichever
occurs first. Replace HP turbine modules
with rearward turbine blade displacement
greater than 0.5 mm.
(ii) For the remaining engines, inspect
within the next 100 hours. Replace HP
turbine modules with rearward turbine blade
displacement greater than 0.5 mm.
Repetitive Inspections
(2) Perform repetitive HP turbine borescope
´
inspections according to Turbomeca S.A.
MSB No. 292 72 2825, Version B, dated
September 21, 2009 or earlier version:
(i) Within 600 hours or 500 cycles from the
previous inspection, whichever occurs first,
if the rearward displacement of the turbine
blades was less than 0.2 mm. Replace HP
turbine modules with rearward turbine blade
displacement greater than 0.5 mm.
(ii) Within 100 hours of the previous
inspection if the rearward displacement of
the turbine blades was between 0.2 mm and
0.5 mm. Replace HP turbine modules with
rearward turbine blade displacement greater
than 0.5 mm.
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(j) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(k) Refer to EASA Airworthiness Directive
2007–0109R1, dated November 9, 2009, and
´
Turbomeca S.A. MSB No. 292 72 2825,
Version B, dated September 21, 2009, or
earlier version, for related information.
(l) Contact Richard Woldan, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803–5299; telephone (781) 238–7136; fax
(781) 238–7199, for more information about
this AD.
Material Incorporated by Reference
´
(m) You must use Turbomeca S.A.
Mandatory Service Bulletin No. 292 72 2825,
Version B, dated September 21, 2009, to do
the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
previously approved the incorporation by
´
reference of Turbomeca S.A. Mandatory
Service Bulletin No. 292 72 2825, dated April
5, 2007, on June 1, 2009 (74 FR 18981, April
27, 2009).
(2) For service information identified in
´
this AD, contact Turbomeca, 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax 33
05 59 74 45 15.
(3) You may review copies at the FAA,
New England Region, 12 New England
Executive Park, Burlington, MA; or 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
September 17, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–23833 Filed 9–24–10; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1100; Directorate
Identifier 2009–NE–37–AD; Amendment 39–
16441; AD 2010–20–07]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines AG V2500–A1, V2522–
A5, V2524–A5, V2525–D5, V2527–A5,
V2527E–A5, V2527M–A5, V2528–D5,
V2530–A5, and V2533–A5 Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
International Aero Engines AG (IAE)
V2500–A1, V2525–D5 and V2528–D5
turbofan engines and certain serial
numbers (S/Ns) of IAE V2522–A5,
V2524–A5, V2527–A5, V2527E–A5,
V2527M–A5, V2530–A5, and V2533–A5
turbofan engines. For certain S/Ns of
V2500–A1, V2522–A5, V2524–A5,
V2527–A5, V2527E–A5, V2527M–A5,
V2530–A5, and V2533–A5 series
turbofan engines, this AD requires
initial and repetitive on-wing ultrasonic
inspections of the high-pressure
compressor (HPC) stage 3 to 8 drum for
cracks. As mandatory terminating action
to the repetitive inspections, this AD
requires removal from service of the
fully silver plated nuts attaching the
HPC stage 3 to 8 drum to the HPC stage
9 to 12 drum, removal of silver residue
from the HPC stage 3 to 8 drum, and
fluorescent penetrant inspection (FPI) of
the stage 3 to 8 drum within a specified
time. For all other engines, this AD
requires removal from service of the
fully silver plated nuts attaching the
HPC stage 3 to 8 drum to the HPC stage
9 to 12 drum, removal of silver residue
from the HPC stage 3 to 8 drum, and FPI
of the HPC stage 3 to 8 drum at the next
drum piece-part exposure. This AD
results from reports of 39 HPC stage 3
to 8 drums found cracked since March
2009. We are issuing this AD to prevent
uncontained failure of the HPC stage 3
to 8 drum, which could result in
damage to the airplane.
DATES: This AD becomes effective
November 1, 2010. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of November 1, 2010.
ADDRESSES: You can get the service
information identified in this AD from
SUMMARY:
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations
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International Aero Engines AG, 400
Main Street, East Hartford, CT 06108;
telephone: (860) 565–5515; fax: (860)
565–5510.
The Docket Operations office is
located at Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
FOR FURTHER INFORMATION CONTACT:
Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: mark.riley@faa.gov; telephone
(781) 238–7758, fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to all IAE V2500–A1, V2525–D5
and V2528–D5 turbofan engines and
certain S/Ns of IAE V2522–A5, V2524–
A5, V2527–A5, V2527E–A5, V2527M–
A5, V2530–A5, and V2533–A5 turbofan
engines. We published the proposed AD
in the Federal Register on February 12,
2010 (75 FR 6860). That action proposed
to require:
• For certain S/Ns of IAE V2500–A1,
V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5,
and V2533–A5 turbofan engines:
Æ Initial and repetitive on-wing
ultrasonic inspections of HPC stage 3 to
8 drums for cracks; and
Æ As mandatory terminating action to
the repetitive ultrasonic inspections,
within 27 months from the effective
date of this AD, removal from service of
the fully silver plated nuts attaching the
HPC stage 3 to 8 drum to the HPC stage
9 to 12 drum, removal of silver residue
from the HPC stage 3 to 8 drums, and
FPI of the HPC stage 3 to 8 drums.
• For all other engines, at the next
piece-part exposure of the HPC stage 3
to 8 drum, removal from service of the
fully silver plated nuts attaching the
HPC stage 3 to 8 drum to the HPC stage
9 to 12 drum, removal of silver residue
from the HPC stage 3 to 8 drums, and
FPI of the HPC stage 3 to 8 drums.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations office (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Mandate Inspection of
Group B and Group C Engines
One commenter, Airbus, requests that
we mandate inspection for the S/N
engines identified in Group B and
Group C of IAE Service Bulletin (SB)
No. V2500–ENG–72–0594, Revision 5,
as these engines may have operated in
a similar environment as the Group A
engines.
We do not agree. Engines identified in
Groups B and C have not exhibited
cracking similar to that seen in engines
listed in Groups A and D. Therefore, it
is not appropriate to mandate
inspections on Group B or C engines at
this time. We did not change the AD.
Claim That Root Cause Is Not Yet
Determined
Airbus claims that the proposed AD
would mandate the inspection only on
engines identified in IAE SB No.
V2500–ENG–72–0594 (Groups A and D)
and IAE SB No. V2500–ENG–72–0603
(Group A) without determining root
cause. To properly identify the suspect
population, determining the root cause
of the HPC stage 3–8 drum cracking is
required.
We do not agree. While we do not yet
know the specific root cause of the
contamination causing the corrosion
cracking of the HPC stage 3–8 drum, we
do know that engines specified in IAE
SB No. V2500–ENG–72–0594 (Groups A
and D) and IAE SB No. V2500–ENG–72–
0603 (Group A) may exhibit HPC stage
3–8 drum corrosion cracking. We did
not change the AD.
Request To Include a Fleetwide
Introduction of a Final Fix
Airbus requests that the proposed AD
should include a fleet-wide introduction
of the final fix (nuts modification), and
in the interim, the ultrasonic inspection,
to correct the cause of HPC stage 3–8
drum cracking for the entire V2500 fleet.
We partially agree. Paragraph (f)(4)(i)
of this AD requires that all operators of
engines requiring these repetitive
ultrasonic inspections remove the fully
silver plated nuts, P/N AS44862, or
equivalent, that attach the HPC stage 3
to 8 drum to the HPC stage 9 to 12
drum, within 27 months after the
effective date of the AD. Paragraph (g)
of this AD also requires those operators
of all other affected engines to remove
the fully silver plated nuts at the next
piece-part exposure of the HPC stage 3–
8 drum after the effective date of the
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AD. Ultrasonic inspection(s) per IAE SB
No. V2500–ENG–72–0594 (Groups A
and D) and IAE SB No. V2500–ENG–72–
0603 only affect certain engines and are
not required for the entire fleet. We did
not change the AD.
Claim That Proposed AD Is Less
Restrictive Than IAE SB
Airbus claims that the proposed AD is
less restrictive than the IAE service
bulletins, and it does not recommend
immediate action for V2500–A5 drums
above 7,545 cycles-since-new and for
V2500–A1 drums above 10,305 cyclessince-new. It therefore does not meet the
criteria for maximum allowable
individual risk per flight.
We do not agree. All ‘‘high cycle’’ HPC
stage 3 to 8 drums in the field that
required inspections at reduced
thresholds, as referenced in the IAE SBs,
have already been inspected. Therefore,
an equivalent level of fleet risk is
maintained for the AD action, and meets
FAA criteria. We did not change the AD.
FAA Should Mandate the Nut Removal
for the Complete V2500 Fleet
Airbus states that the proposed AD
does not put a compliance date for
removal of the fully plated silver nuts
for the complete V2500 fleet. Removal
of the fully silver plated nuts should be
mandated for the complete V2500 fleet.
We agree that the fully silver plated
nuts should be removed from service for
the entire V2500 fleet. However, all
engines do not need to be retrofitted
before a specific compliance date.
V2500 engines that have been
determined to require repetitive
ultrasonic inspections are at an elevated
risk level, and therefore require removal
of the fully silver plated nuts within a
specified time period to prevent
corrosion and potential failure of the
HPC 3–8 drum. The remaining V2500
engines that do not require repetitive
ultrasonic inspections have been
determined to be at a much lower risk
level, and therefore, are only required to
have the fully silver plated nuts
removed at the next piece part exposure.
We did not change the AD.
Request To Reference the Latest Service
Bulletins
IAE and Japan Airlines request that
we reference the latest revisions of the
service bulletins, which are IAE SB No.
V2500–ENG–72–0594, Revision 6, IAE
SB No. V2500–ENG–72–0603, Revision
2, and V2500–ENG–72–0601, Revision
2, as they have been updated to include
additional engine S/Ns and other
clarification changes.
We agree. We changed the AD to
reference the revised service bulletins.
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations
Request To Correct Typos in the
Proposed AD
Two commenters request that we
change the following:
Paragraph (f)(4) should be revised
from ‘‘HPC Stage 8 to 12 drum’’ to ‘‘HPC
Stage 3 to 8 drum’’.
Paragraphs (f)(1), (f)(4)(ii), and (g)(2)
should be revised from ‘‘using paragraph
3 of the Accomplishment Instructions
of’’ to ‘‘using the paragraph 3
Accomplishment Instructions of’’.
We partially agree. We agree that
paragraph (f)(4) should be revised from
‘‘HPC Stage 8 to 12 drum’’ to ‘‘HPC Stage
3 to 8 drum,’’ We changed the AD.
We also agree that our reference in
paragraphs (f)(1), (f)(4)(ii), and (g)(2)
should be revised, but not as
recommended. We changed paragraphs
(f)(1), (f)(4)(ii), and (g)(2) from ‘‘using
paragraph 3 of the Accomplishment
Instructions of’’ to ‘‘use IAE SB No.
V2500–ENG–72–0601, Revision 2, dated
April 12, 2010, Accomplishment
Instructions, paragraph 3.’’
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Material Incorporated by Reference
Section Missing From Proposed AD
One commenter states that paragraphs
(f)(1), (f)(4)(ii), and (g)(2) require
ultrasonic inspection and cleaning to be
performed using the Accomplishment
Instructions of specified revisions of
IAE SBs V2500–ENG–72–0594, V2500–
ENG–603, and V2500–ENG–72–0601.
These SBs should be listed in the
Material Incorporated by Reference
section, which is missing from the
NPRM.
We agree. This Final Rule AD
includes the Material Incorporated by
Reference section, which includes those
SBs.
Request To Revise the Relevant Service
Information
IAE commented to revise the last
sentence of the ‘‘Relevant Service
Information’’ in the preamble of the AD
to change: ‘‘* * * 27 months from the
effective date of the proposed AD’’ to ‘‘27
months after the effective date of this
AD’’. The commenter states that this
could be interpreted incorrectly as 27
months from February 12, 2010 (date of
the NPRM).
We do not agree that the compliance
date could be misinterpreted. Paragraph
(4) of this AD correctly states ‘‘27
months after the effective date of this
AD.’’ We did not change the AD.
Request To Revise the Mandatory
Terminating Action Compliance Time
IAE requests that we revise the
mandatory terminating action
compliance time of ‘‘27 months after the
effective date of this AD’’ to a calendar
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16:28 Sep 24, 2010
Jkt 220001
end date of October 31, 2012, to be
consistent with the IAE risk assessment.
We do not agree. Due to the
uncertainty of the actual publication
date of the AD, revising the mandatory
terminating action from 27 months after
the effective date of this AD to a
calendar date of October 31, 2012, may
result in a compliance time that is more
restrictive than what was proposed in
the NPRM. We did not change the AD.
Request To Revise the Definition of
Piece-Part Exposure
IAE requests that we revise the AD to
change paragraph (i) of the definition of
piece-part exposure for the HPC stage 3
to 8 drum from ‘‘removal of the drum
from the engine and removal of all
blades from the drum’’ to ‘‘separation of
the rotating drum hardware from the
static cases and removal of all blades
from the HPC stage 3 to 8 drum’’. IAE
is concerned that confusion could occur
with the current statement.
We do not agree. The current
description is accurate. We did not
change the AD.
Request To Eliminate the Mandatory
Terminating Action
One commenter requests that we
revise paragraph (f)(4) of the AD to
eliminate the 27-month mandatory
terminating action requirement to
remove the fully silver plated nuts that
attach the HPC stage 3 to 8 drum to the
HPC stage 9 to 12 drum. The commenter
states that performing repetitive
ultrasonic inspections will provide an
acceptable level of safety, and that
incorporation of the 27-month
mandatory terminating action
requirement is an unacceptable cost
burden to operators.
We do not agree. We have determined
that removal of the fully silver plated
nuts within 27 months from the
effective date of the AD is required to
maintain an acceptable level of safety.
We did not change the AD.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
848 IAE V2500–A1, V2522–A5, V2524–
A5, V2525–D5, V2527–A5, V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5,
and V2533–A5 turbofan engines
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59069
installed on airplanes of U.S. registry.
We estimate that 29 of these engines
will require ultrasonic inspections, and
that it will take about 3 work-hours per
engine to perform one ultrasonic
inspection. We estimate that it will take
about 2 work-hours per engine to
perform the FPI of the HPC stage 3 to
8 drum, and that the average labor rate
is $85 per work-hour. We also estimate
that removal of silver residue from the
engine will cost about $2,600 per
engine. Required parts will cost about
$795 per engine. Based on these figures,
we estimate the total cost of the AD to
U.S. operators to be $3,030,515.
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); and
(3) 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.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations
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 Federal Aviation Administration
amends 14 CFR part 39 as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2010–20–07 International Aero Engines
AG: Amendment 39–16441. Docket No.
FAA–2009–1100; Directorate Identifier
2009–NE–37–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 1, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) All International Aero Engines AG (IAE)
V2500–A1 turbofan engines; and
(2) All IAE V2525–D5 and V2528–D5
turbofan engines; and
(3) IAE V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5, and
V2533–A5 turbofan engines with serial
numbers (S/Ns) up to and including V13181,
and with S/Ns from V15000 up to and
including V15245.
(4) These engines are installed on, but not
limited to, Airbus A319, A320, and A321,
and McDonnell Douglas MD–90 airplanes.
Unsafe Condition
(d) This AD results from reports of 39 highpressure compressor (HPC) stage 3 to 8
drums found cracked since March 2009. We
are issuing this AD to prevent uncontained
failure of the HPC stage 3 to 8 drum, which
could result in damage to the airplane.
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Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Engines Requiring Ultrasonic Inspections of
the HPC Stage 3 to 8 Drum
(f) For IAE V2522–A5, V2524–A5, V2527–
A5, V2527E–A5, V2527M–A5, V2530–A5,
and V2533–A5 turbofan engines with S/Ns in
‘‘Group A’’ or ‘‘Group D’’ in IAE Service
Bulletin (SB) No. V2500–ENG–72–0594,
Revision 6, dated April 12, 2010, and for
V2500–A1 turbofan engines with S/Ns in
‘‘Group A’’ in IAE SB No. V2500–ENG–72–
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16:28 Sep 24, 2010
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0603, Revision 2, dated March 17, 2010, do
the following:
(1) Perform an initial ultrasonic inspection
of the HPC stage 3 to 8 drum using IAE SB
No. V2500–ENG–72–0594, Revision 6, dated
April 12, 2010, Accomplishment
Instructions, paragraph 3, or IAE SB No.
V2500–ENG–72–0603, Revision 2, dated
March 17, 2010, Accomplishment
Instructions, paragraph 3, before
accumulating 5,200 cycles-since-new (CSN)
or within 500 cycles from the effective date
of this AD, whichever occurs later.
(2) Thereafter, perform repetitive ultrasonic
inspections of the HPC stage 3 to 8 drum for
cracks within every 500 cycles-since-lastinspection.
(3) If cracks or crack indications are
identified, remove the drum from service
before further flight.
Mandatory Terminating Action
(4) As mandatory terminating action to the
repetitive inspections required by this AD, at
the next engine shop visit, but no later than
27 months after the effective date of this AD,
do the following before returning any HPC
stage 3 to 8 drum to service:
(i) Remove from service fully silver plated
nuts, part number (P/N) AS44862 or
equivalent, that attach the HPC stage 3 to 8
drum to the HPC stage 9 to 12 drum.
(ii) Remove the silver residue from the HPC
stage 3 to 8 drum using the IAE SB No.
V2500–ENG–72–0601, Revision 2, dated
April 12, 2010, Accomplishment
Instructions, paragraph 3. Drums cleaned
before the effective date of this AD using
engine manual task 72–41–11–110–001
satisfy this requirement.
(iii) Fluorescent penetrant inspect (FPI) the
HPC stage 3 to 8 drum for cracks, and remove
from service any drum found cracked. You
can find guidance on performing an FPI of
the HPC stage 3 to 8 drum in IAE engine
manual task 72–41–11–200–001.
(iv) Installation of a zero-time HPC stage 3
to 8 drum or a drum that has never operated
with fully silver plated nuts, P/N AS44862 or
equivalent, that attach the HPC stage 3 to 8
drum to the HPC stage 9 to 12 drum
eliminates the need for the cleaning and FPI
required by paragraphs (f)(4)(ii) and (f)(4)(iii)
of this AD.
All Other Engines
(g) For all other engines, at the next piecepart exposure of the HPC stage 3 to 8 drum
after the effective date of this AD, do the
following before returning the drum to
service:
(1) Remove from service fully silver plated
nuts, P/N AS44862 or equivalent, that attach
the HPC stage 3 to 8 drum to the HPC stage
9 to 12 drum.
(2) Remove the silver residue from the HPC
stage 3 to 8 drum using IAE SB No. V2500–
ENG–72–0601, Revision 2, dated April 12,
2010, Accomplishment Instructions,
paragraph 3. Drums cleaned before the
effective date of this AD using engine manual
task 72–41–11–110–001 satisfy this
requirement.
(3) FPI the HPC stage 3 to 8 drum for
cracks, and remove from service any drum
found cracked. You can find guidance on
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
performing an FPI of the HPC stage 3 to 8
drum in IAE engine manual task 72–41–11–
200–001.
(4) Installation of a zero-time HPC stage 3
to 8 drum or a drum that has never operated
with fully silver plated nuts, P/N AS44862 or
equivalent, that attach the HPC stage 3 to 8
drum to the HPC stage 9 to 12 drum
eliminates the need for the cleaning and FPI
required by paragraphs (g)(2) and (g)(3) of
this AD.
Definitions
(h) For the purpose of this AD, an engine
shop visit is the induction of an engine into
the shop for maintenance involving the
separation of a pair of major mating engine
flanges, except that the separation of engine
flanges solely for the purposes of
transportation without subsequent engine
maintenance is not an engine shop visit.
(i) For the purpose of this AD, piece-part
exposure is removal of the HPC stage 3 to 8
drum from the engine and removal of all
blades from the drum.
Previous Credit
(j) Initial or repetitive ultrasonic
inspections of the HPC stage 3 to 8 drum
using IAE SB No. V2500–ENG–72–0594,
Revision 3, dated August 7, 2009, or Revision
4, dated October 13, 2009, or Revision 5,
dated November 23, 2009, before the effective
date of this AD, meets the inspection
requirements of paragraphs (f)(1) through
(f)(3) of this AD.
(k) Initial or repetitive ultrasonic
inspections of the HPC stage 3 to 8 drum
using IAE SB No. V2500–ENG–72–0603,
Original Issue, dated November 24 2009, or
Revision 1, dated December 18, 2009, before
the effective date of this AD, meets the
inspection requirements of paragraphs (f)(1)
through (f)(3) of this AD.
Alternative Methods of Compliance
(AMOCS)
(l) The Manager, Engine Certification
Office, has the authority to approve AMOCs
for this AD if requested using the procedures
found in 14 CFR 39.19.
Related Information
(m) Contact Mark Riley, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: mark.riley@faa.gov; telephone
(781) 238–7758, fax (781) 238–7199, for more
information about this AD.
(n) Contact International Aero Engines AG,
400 Main Street, East Hartford, CT 06108;
telephone: (860) 565–5515; fax: (860) 565–
5510, for a copy of the service information
referenced in this AD.
Material Incorporated by Reference
(o) You must use the service information
specified in the following Table 1 to perform
the inspections and silver residue removal
required by this AD. The Director of the
Federal Register approved the incorporation
by reference of the documents listed in the
following Table 1 in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact
International Aero Engines AG, 400 Main
Street, East Hartford, CT 06108; telephone:
E:\FR\FM\27SER1.SGM
27SER1
Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations
Burlington, MA; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
(860) 565–5515; fax: (860) 565–5510, for a
copy of this service information. You may
review copies at the FAA, New England
Region, 12 New England Executive Park,
59071
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
TABLE 1—INCORPORATION BY REFERENCE
International Aero Engines Service Bulletin No.
Page
V2500–ENG–72–0594 ......................................................................................................................
Total Pages: 61.
V2500–ENG–72–0601 ......................................................................................................................
Total Pages: 9.
V2500–ENG–72–0603 ......................................................................................................................
Total pages: 46.
ALL ......
6
April 12, 2010.
ALL ......
2
April 12, 2010.
ALL ......
2
March 17, 2010.
damage to the aircraft and, if deployment was
activated by a dual engine shutdown, could
also result in loss of hydraulic power for the
flight controls [and consequent reduced
ability of the flightcrew to maintain the safe
flight and landing of the airplane].
Issued in Burlington, Massachusetts, on
September 15, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–23832 Filed 9–24–10; 8:45 am]
*
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0439; Directorate
Identifier 2010–NM–029–AD; Amendment
39–16437; AD 2010–20–03]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model CL–600–2B16 (CL–604
Variants (Including CL–605 Marketing
Variant)) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
mstockstill on DSKH9S0YB1PROD with RULES
SUMMARY:
Following five reported cases of * * *
balance washer screw failure on similar
ADGs [air-driven generators]/ram air turbines
installed on other aircraft types, investigation
by Hamilton Sundstrand determined that a
specific batch of the screws had a
metallographic non-conformity that
increased their susceptibility to brittle
fracture. * * *
Failure of a balance washer screw can
result in loss of the related balance washer,
with consequent turbine imbalance. Such
imbalance could potentially result in ADG
structural failure (including blade failure),
loss of ADG electrical power and structural
VerDate Mar<15>2010
16:28 Sep 24, 2010
Jkt 220001
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
November 1, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 1, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Christopher Alfano, Aerospace
Engineer, Airframe and Mechanical
Systems Branch, ANE–171, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7340; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 2, 2010 (75 FR 30740).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Following five reported cases of * * *
balance washer screw failure on similar
ADGs [air-driven generators]/ram air turbines
installed on other aircraft types, investigation
by Hamilton Sundstrand determined that a
specific batch of the screws had a
metallographic non-conformity that
increased their susceptibility to brittle
fracture. Subsequently, it was established
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Revision
Date
that 152 ‘‘dry’’ ADGs [Hamilton Sundstrand
Part Numbers (P/Ns) in the 761339 series and
1711405; see Note] either had nonconforming screws installed during
production or possibly during maintenance
or repair at Hamilton Sundstrand repair
stations.
Failure of a balance washer screw can
result in loss of the related balance washer,
with consequent turbine imbalance. Such
imbalance could potentially result in ADG
structural failure (including blade failure),
loss of ADG electrical power and structural
damage to the aircraft and, if deployment was
activated by a dual engine shutdown, could
also result in loss of hydraulic power for the
flight controls [and consequent reduced
ability of the flightcrew to maintain the safe
flight and landing of the airplane].
This [Canadian] directive mandates
checking of the ADG and replacing the
balance washer screws, if required. It also
prohibits future installation of unmodified
ADGs.
Note: ADGs with Hamilton Sundstrand
P/Ns in the 761339 series and 1711405 are
installed on the aircraft model listed in the
Applicability section above in addition to
Bombardier Inc. Models CL–600–2B19, CL–
600–2C10 and CL–600–2D24. The latter three
models are covered in a separate directive.
You may obtain further information
by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
E:\FR\FM\27SER1.SGM
27SER1
]]>Agencies
[Federal Register Volume 75, Number 186 (Monday, September 27, 2010)]
[Rules and Regulations]
[Pages 59067-59071]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-23832]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1100; Directorate Identifier 2009-NE-37-AD;
Amendment 39-16441; AD 2010-20-07]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG V2500-A1,
V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5,
V2530-A5, and V2533-A5 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
International Aero Engines AG (IAE) V2500-A1, V2525-D5 and V2528-D5
turbofan engines and certain serial numbers (S/Ns) of IAE V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5
turbofan engines. For certain S/Ns of V2500-A1, V2522-A5, V2524-A5,
V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 series turbofan
engines, this AD requires initial and repetitive on-wing ultrasonic
inspections of the high-pressure compressor (HPC) stage 3 to 8 drum for
cracks. As mandatory terminating action to the repetitive inspections,
this AD requires removal from service of the fully silver plated nuts
attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum,
removal of silver residue from the HPC stage 3 to 8 drum, and
fluorescent penetrant inspection (FPI) of the stage 3 to 8 drum within
a specified time. For all other engines, this AD requires removal from
service of the fully silver plated nuts attaching the HPC stage 3 to 8
drum to the HPC stage 9 to 12 drum, removal of silver residue from the
HPC stage 3 to 8 drum, and FPI of the HPC stage 3 to 8 drum at the next
drum piece-part exposure. This AD results from reports of 39 HPC stage
3 to 8 drums found cracked since March 2009. We are issuing this AD to
prevent uncontained failure of the HPC stage 3 to 8 drum, which could
result in damage to the airplane.
DATES: This AD becomes effective November 1, 2010. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of November 1, 2010.
ADDRESSES: You can get the service information identified in this AD
from
[[Page 59068]]
International Aero Engines AG, 400 Main Street, East Hartford, CT
06108; telephone: (860) 565-5515; fax: (860) 565-5510.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
mark.riley@faa.gov; telephone (781) 238-7758, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to all IAE V2500-A1, V2525-
D5 and V2528-D5 turbofan engines and certain S/Ns of IAE V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5
turbofan engines. We published the proposed AD in the Federal Register
on February 12, 2010 (75 FR 6860). That action proposed to require:
For certain S/Ns of IAE V2500-A1, V2522-A5, V2524-A5,
V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan
engines:
[cir] Initial and repetitive on-wing ultrasonic inspections of HPC
stage 3 to 8 drums for cracks; and
[cir] As mandatory terminating action to the repetitive ultrasonic
inspections, within 27 months from the effective date of this AD,
removal from service of the fully silver plated nuts attaching the HPC
stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver
residue from the HPC stage 3 to 8 drums, and FPI of the HPC stage 3 to
8 drums.
For all other engines, at the next piece-part exposure of
the HPC stage 3 to 8 drum, removal from service of the fully silver
plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to
12 drum, removal of silver residue from the HPC stage 3 to 8 drums, and
FPI of the HPC stage 3 to 8 drums.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
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 Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Mandate Inspection of Group B and Group C Engines
One commenter, Airbus, requests that we mandate inspection for the
S/N engines identified in Group B and Group C of IAE Service Bulletin
(SB) No. V2500-ENG-72-0594, Revision 5, as these engines may have
operated in a similar environment as the Group A engines.
We do not agree. Engines identified in Groups B and C have not
exhibited cracking similar to that seen in engines listed in Groups A
and D. Therefore, it is not appropriate to mandate inspections on Group
B or C engines at this time. We did not change the AD.
Claim That Root Cause Is Not Yet Determined
Airbus claims that the proposed AD would mandate the inspection
only on engines identified in IAE SB No. V2500-ENG-72-0594 (Groups A
and D) and IAE SB No. V2500-ENG-72-0603 (Group A) without determining
root cause. To properly identify the suspect population, determining
the root cause of the HPC stage 3-8 drum cracking is required.
We do not agree. While we do not yet know the specific root cause
of the contamination causing the corrosion cracking of the HPC stage 3-
8 drum, we do know that engines specified in IAE SB No. V2500-ENG-72-
0594 (Groups A and D) and IAE SB No. V2500-ENG-72-0603 (Group A) may
exhibit HPC stage 3-8 drum corrosion cracking. We did not change the
AD.
Request To Include a Fleetwide Introduction of a Final Fix
Airbus requests that the proposed AD should include a fleet-wide
introduction of the final fix (nuts modification), and in the interim,
the ultrasonic inspection, to correct the cause of HPC stage 3-8 drum
cracking for the entire V2500 fleet.
We partially agree. Paragraph (f)(4)(i) of this AD requires that
all operators of engines requiring these repetitive ultrasonic
inspections remove the fully silver plated nuts, P/N AS44862, or
equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9 to
12 drum, within 27 months after the effective date of the AD. Paragraph
(g) of this AD also requires those operators of all other affected
engines to remove the fully silver plated nuts at the next piece-part
exposure of the HPC stage 3-8 drum after the effective date of the AD.
Ultrasonic inspection(s) per IAE SB No. V2500-ENG-72-0594 (Groups A and
D) and IAE SB No. V2500-ENG-72-0603 only affect certain engines and are
not required for the entire fleet. We did not change the AD.
Claim That Proposed AD Is Less Restrictive Than IAE SB
Airbus claims that the proposed AD is less restrictive than the IAE
service bulletins, and it does not recommend immediate action for
V2500-A5 drums above 7,545 cycles-since-new and for V2500-A1 drums
above 10,305 cycles-since-new. It therefore does not meet the criteria
for maximum allowable individual risk per flight.
We do not agree. All ``high cycle'' HPC stage 3 to 8 drums in the
field that required inspections at reduced thresholds, as referenced in
the IAE SBs, have already been inspected. Therefore, an equivalent
level of fleet risk is maintained for the AD action, and meets FAA
criteria. We did not change the AD.
FAA Should Mandate the Nut Removal for the Complete V2500 Fleet
Airbus states that the proposed AD does not put a compliance date
for removal of the fully plated silver nuts for the complete V2500
fleet. Removal of the fully silver plated nuts should be mandated for
the complete V2500 fleet.
We agree that the fully silver plated nuts should be removed from
service for the entire V2500 fleet. However, all engines do not need to
be retrofitted before a specific compliance date. V2500 engines that
have been determined to require repetitive ultrasonic inspections are
at an elevated risk level, and therefore require removal of the fully
silver plated nuts within a specified time period to prevent corrosion
and potential failure of the HPC 3-8 drum. The remaining V2500 engines
that do not require repetitive ultrasonic inspections have been
determined to be at a much lower risk level, and therefore, are only
required to have the fully silver plated nuts removed at the next piece
part exposure. We did not change the AD.
Request To Reference the Latest Service Bulletins
IAE and Japan Airlines request that we reference the latest
revisions of the service bulletins, which are IAE SB No. V2500-ENG-72-
0594, Revision 6, IAE SB No. V2500-ENG-72-0603, Revision 2, and V2500-
ENG-72-0601, Revision 2, as they have been updated to include
additional engine S/Ns and other clarification changes.
We agree. We changed the AD to reference the revised service
bulletins.
[[Page 59069]]
Request To Correct Typos in the Proposed AD
Two commenters request that we change the following:
Paragraph (f)(4) should be revised from ``HPC Stage 8 to 12 drum''
to ``HPC Stage 3 to 8 drum''.
Paragraphs (f)(1), (f)(4)(ii), and (g)(2) should be revised from
``using paragraph 3 of the Accomplishment Instructions of'' to ``using
the paragraph 3 Accomplishment Instructions of''.
We partially agree. We agree that paragraph (f)(4) should be
revised from ``HPC Stage 8 to 12 drum'' to ``HPC Stage 3 to 8 drum,''
We changed the AD.
We also agree that our reference in paragraphs (f)(1), (f)(4)(ii),
and (g)(2) should be revised, but not as recommended. We changed
paragraphs (f)(1), (f)(4)(ii), and (g)(2) from ``using paragraph 3 of
the Accomplishment Instructions of'' to ``use IAE SB No. V2500-ENG-72-
0601, Revision 2, dated April 12, 2010, Accomplishment Instructions,
paragraph 3.''
Material Incorporated by Reference Section Missing From Proposed AD
One commenter states that paragraphs (f)(1), (f)(4)(ii), and (g)(2)
require ultrasonic inspection and cleaning to be performed using the
Accomplishment Instructions of specified revisions of IAE SBs V2500-
ENG-72-0594, V2500-ENG-603, and V2500-ENG-72-0601. These SBs should be
listed in the Material Incorporated by Reference section, which is
missing from the NPRM.
We agree. This Final Rule AD includes the Material Incorporated by
Reference section, which includes those SBs.
Request To Revise the Relevant Service Information
IAE commented to revise the last sentence of the ``Relevant Service
Information'' in the preamble of the AD to change: ``* * * 27 months
from the effective date of the proposed AD'' to ``27 months after the
effective date of this AD''. The commenter states that this could be
interpreted incorrectly as 27 months from February 12, 2010 (date of
the NPRM).
We do not agree that the compliance date could be misinterpreted.
Paragraph (4) of this AD correctly states ``27 months after the
effective date of this AD.'' We did not change the AD.
Request To Revise the Mandatory Terminating Action Compliance Time
IAE requests that we revise the mandatory terminating action
compliance time of ``27 months after the effective date of this AD'' to
a calendar end date of October 31, 2012, to be consistent with the IAE
risk assessment.
We do not agree. Due to the uncertainty of the actual publication
date of the AD, revising the mandatory terminating action from 27
months after the effective date of this AD to a calendar date of
October 31, 2012, may result in a compliance time that is more
restrictive than what was proposed in the NPRM. We did not change the
AD.
Request To Revise the Definition of Piece-Part Exposure
IAE requests that we revise the AD to change paragraph (i) of the
definition of piece-part exposure for the HPC stage 3 to 8 drum from
``removal of the drum from the engine and removal of all blades from
the drum'' to ``separation of the rotating drum hardware from the
static cases and removal of all blades from the HPC stage 3 to 8
drum''. IAE is concerned that confusion could occur with the current
statement.
We do not agree. The current description is accurate. We did not
change the AD.
Request To Eliminate the Mandatory Terminating Action
One commenter requests that we revise paragraph (f)(4) of the AD to
eliminate the 27-month mandatory terminating action requirement to
remove the fully silver plated nuts that attach the HPC stage 3 to 8
drum to the HPC stage 9 to 12 drum. The commenter states that
performing repetitive ultrasonic inspections will provide an acceptable
level of safety, and that incorporation of the 27-month mandatory
terminating action requirement is an unacceptable cost burden to
operators.
We do not agree. We have determined that removal of the fully
silver plated nuts within 27 months from the effective date of the AD
is required to maintain an acceptable level of safety. We did not
change the AD.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 848 IAE V2500-A1, V2522-A5,
V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5,
and V2533-A5 turbofan engines installed on airplanes of U.S. registry.
We estimate that 29 of these engines will require ultrasonic
inspections, and that it will take about 3 work-hours per engine to
perform one ultrasonic inspection. We estimate that it will take about
2 work-hours per engine to perform the FPI of the HPC stage 3 to 8
drum, and that the average labor rate is $85 per work-hour. We also
estimate that removal of silver residue from the engine will cost about
$2,600 per engine. Required parts will cost about $795 per engine.
Based on these figures, we estimate the total cost of the AD to U.S.
operators to be $3,030,515.
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); and
(3) 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
[[Page 59070]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2010-20-07 International Aero Engines AG: Amendment 39-16441. Docket
No. FAA-2009-1100; Directorate Identifier 2009-NE-37-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
1, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) All International Aero Engines AG (IAE) V2500-A1 turbofan
engines; and
(2) All IAE V2525-D5 and V2528-D5 turbofan engines; and
(3) IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5,
V2530-A5, and V2533-A5 turbofan engines with serial numbers (S/Ns)
up to and including V13181, and with S/Ns from V15000 up to and
including V15245.
(4) These engines are installed on, but not limited to, Airbus
A319, A320, and A321, and McDonnell Douglas MD-90 airplanes.
Unsafe Condition
(d) This AD results from reports of 39 high-pressure compressor
(HPC) stage 3 to 8 drums found cracked since March 2009. We are
issuing this AD to prevent uncontained failure of the HPC stage 3 to
8 drum, which could result in damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Engines Requiring Ultrasonic Inspections of the HPC Stage 3 to 8 Drum
(f) For IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5,
V2530-A5, and V2533-A5 turbofan engines with S/Ns in ``Group A'' or
``Group D'' in IAE Service Bulletin (SB) No. V2500-ENG-72-0594,
Revision 6, dated April 12, 2010, and for V2500-A1 turbofan engines
with S/Ns in ``Group A'' in IAE SB No. V2500-ENG-72-0603, Revision
2, dated March 17, 2010, do the following:
(1) Perform an initial ultrasonic inspection of the HPC stage 3
to 8 drum using IAE SB No. V2500-ENG-72-0594, Revision 6, dated
April 12, 2010, Accomplishment Instructions, paragraph 3, or IAE SB
No. V2500-ENG-72-0603, Revision 2, dated March 17, 2010,
Accomplishment Instructions, paragraph 3, before accumulating 5,200
cycles-since-new (CSN) or within 500 cycles from the effective date
of this AD, whichever occurs later.
(2) Thereafter, perform repetitive ultrasonic inspections of the
HPC stage 3 to 8 drum for cracks within every 500 cycles-since-last-
inspection.
(3) If cracks or crack indications are identified, remove the
drum from service before further flight.
Mandatory Terminating Action
(4) As mandatory terminating action to the repetitive
inspections required by this AD, at the next engine shop visit, but
no later than 27 months after the effective date of this AD, do the
following before returning any HPC stage 3 to 8 drum to service:
(i) Remove from service fully silver plated nuts, part number
(P/N) AS44862 or equivalent, that attach the HPC stage 3 to 8 drum
to the HPC stage 9 to 12 drum.
(ii) Remove the silver residue from the HPC stage 3 to 8 drum
using the IAE SB No. V2500-ENG-72-0601, Revision 2, dated April 12,
2010, Accomplishment Instructions, paragraph 3. Drums cleaned before
the effective date of this AD using engine manual task 72-41-11-110-
001 satisfy this requirement.
(iii) Fluorescent penetrant inspect (FPI) the HPC stage 3 to 8
drum for cracks, and remove from service any drum found cracked. You
can find guidance on performing an FPI of the HPC stage 3 to 8 drum
in IAE engine manual task 72-41-11-200-001.
(iv) Installation of a zero-time HPC stage 3 to 8 drum or a drum
that has never operated with fully silver plated nuts, P/N AS44862
or equivalent, that attach the HPC stage 3 to 8 drum to the HPC
stage 9 to 12 drum eliminates the need for the cleaning and FPI
required by paragraphs (f)(4)(ii) and (f)(4)(iii) of this AD.
All Other Engines
(g) For all other engines, at the next piece-part exposure of
the HPC stage 3 to 8 drum after the effective date of this AD, do
the following before returning the drum to service:
(1) Remove from service fully silver plated nuts, P/N AS44862 or
equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9
to 12 drum.
(2) Remove the silver residue from the HPC stage 3 to 8 drum
using IAE SB No. V2500-ENG-72-0601, Revision 2, dated April 12,
2010, Accomplishment Instructions, paragraph 3. Drums cleaned before
the effective date of this AD using engine manual task 72-41-11-110-
001 satisfy this requirement.
(3) FPI the HPC stage 3 to 8 drum for cracks, and remove from
service any drum found cracked. You can find guidance on performing
an FPI of the HPC stage 3 to 8 drum in IAE engine manual task 72-41-
11-200-001.
(4) Installation of a zero-time HPC stage 3 to 8 drum or a drum
that has never operated with fully silver plated nuts, P/N AS44862
or equivalent, that attach the HPC stage 3 to 8 drum to the HPC
stage 9 to 12 drum eliminates the need for the cleaning and FPI
required by paragraphs (g)(2) and (g)(3) of this AD.
Definitions
(h) For the purpose of this AD, an engine shop visit is the
induction of an engine into the shop for maintenance involving the
separation of a pair of major mating engine flanges, except that the
separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance is not an
engine shop visit.
(i) For the purpose of this AD, piece-part exposure is removal
of the HPC stage 3 to 8 drum from the engine and removal of all
blades from the drum.
Previous Credit
(j) Initial or repetitive ultrasonic inspections of the HPC
stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0594, Revision 3,
dated August 7, 2009, or Revision 4, dated October 13, 2009, or
Revision 5, dated November 23, 2009, before the effective date of
this AD, meets the inspection requirements of paragraphs (f)(1)
through (f)(3) of this AD.
(k) Initial or repetitive ultrasonic inspections of the HPC
stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0603, Original
Issue, dated November 24 2009, or Revision 1, dated December 18,
2009, before the effective date of this AD, meets the inspection
requirements of paragraphs (f)(1) through (f)(3) of this AD.
Alternative Methods of Compliance (AMOCS)
(l) The Manager, Engine Certification Office, has the authority
to approve AMOCs for this AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(m) Contact Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov;
telephone (781) 238-7758, fax (781) 238-7199, for more information
about this AD.
(n) Contact International Aero Engines AG, 400 Main Street, East
Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510,
for a copy of the service information referenced in this AD.
Material Incorporated by Reference
(o) You must use the service information specified in the
following Table 1 to perform the inspections and silver residue
removal required by this AD. The Director of the Federal Register
approved the incorporation by reference of the documents listed in
the following Table 1 in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact International Aero Engines AG, 400 Main Street,
East Hartford, CT 06108; telephone:
[[Page 59071]]
(860) 565-5515; fax: (860) 565-5510, for a copy of this service
information. You may review copies at the FAA, New England Region,
12 New England Executive Park, Burlington, MA; or 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.
Table 1--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
International Aero Engines Service
Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
V2500-ENG-72-0594...................... ALL.................. 6 April 12, 2010.
Total Pages: 61....................
V2500-ENG-72-0601...................... ALL.................. 2 April 12, 2010.
Total Pages: 9.....................
V2500-ENG-72-0603...................... ALL.................. 2 March 17, 2010.
Total pages: 46....................
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on September 15, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-23832 Filed 9-24-10; 8:45 am]
BILLING CODE 4910-13-P
