Airworthiness Directives; CFM International CFM56-5 and -5B Series Turbofan Engines, 6457-6459 [E7-2068]
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Federal Register / Vol. 72, No. 28 / Monday, February 12, 2007 / Rules and Regulations
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27112; Directorate
Identifier 2001–NE–49–AD; Amendment 39–
14926; AD 2007–03–15]
RIN 2120–AA64
Airworthiness Directives; CFM
International CFM56–5 and –5B Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD) for
CFM International CFM56–5 and –5B
series turbofan engines. That AD
requires exhaust gas temperature (EGT)
harness replacement or the
establishment of an EGT baseline and
trend monitoring. That AD also requires
replacement, if necessary, of certain
EGT harnesses and EGT couplings as
soon as a slow and continuous EGT drift
downward is noticed after the effective
date of that AD. This AD requires the
same actions but for an increased
population of affected EGT harnesses.
This AD results from CFM International
adding subsequently certified engine
models to the list of engines that could
have affected harnesses installed. We
are issuing this AD to prevent
unexpected deterioration of critical
rotating engine parts due to higher than
desired engine operating EGTs.
DATES: This AD becomes effective
March 19, 2007. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of March 19, 2007.
ADDRESSES: You can get the service
information identified in this AD from
CFM International, Technical
Publications Department, 1 Neumann
Way, Cincinnati, OH 45215; telephone
(513) 552–2800; fax (513) 552–2816.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
James Rosa, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
telephone (781) 238–7152; fax (781)
238–7199; e-mail: james.rosa@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
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15:23 Feb 09, 2007
Jkt 211001
a proposed AD. The proposed AD
applies to CFM International CFM56–5
and –5B series turbofan engines. We
published the proposed AD in the
Federal Register on June 16, 2006 (71
FR 34852). That action proposed to
require, for an increased population of
affected EGT harnesses:
• EGT harness replacement or the
establishment of an EGT baseline and
trend monitoring; and
• Replacement, if necessary, of
certain EGT harnesses and EGT
couplings as soon as a slow and
continuous EGT drift downward is
noticed after the effective date of that
AD.
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.
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
SUMMARY:
6457
Regulatory Findings
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
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.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Docket Number Change
We are transferring the docket for this
AD to the Docket Management System
as part of our on-going docket
management consolidation efforts. The
new Docket No. is FAA–2007–27112.
The old Docket No. became the
Directorate Identifier, which is 2001–
NE–49–AD. This AD might get logged
into the DMS docket, ahead of the
previously collected documents from
the old docket file, as we are in the
process of sending those items to the
DMS.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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
PO 00000
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Fmt 4700
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13020 (68 FR
3171, January 23, 2003) and by adding
a new airworthiness directive,
I
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6458
Federal Register / Vol. 72, No. 28 / Monday, February 12, 2007 / Rules and Regulations
Amendment 39–14926, to read as
follows:
2007–03–15 CFM International:
Amendment 39–14926; Docket No.
FAA–2007–27112; Directorate Identifier
2001–NE–49–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 19, 2007.
CFM56–5B3/P1, CFM56–5B3/2P1, CFM56–
5B4/P1, and CFM56–5B4/2P1, to the list of
engines that could have affected harnesses
installed, and increasing the population of
affected EGT harnesses. We are issuing this
AD to prevent unexpected deterioration of
critical rotating engine parts due to higher
than desired engine operating EGTs.
Applicability
(c) This AD applies to CFM International
CFM56–5 and –5B series turbofan engines:
(1) With an exhaust gas temperature (EGT)
upper harness part number (P/N) CA170–00,
with a serial number (SN):
(i) Listed in Table 1, Table 4, or Table 5
of CFM56 Service Bulletin (SB) No. CFM56–
5B S/B 77–0008, Revision 3, dated April 4,
2005, or
(ii) Listed in Table 1 or Table 4 of CFM56
SB No. CFM56–5 S/B 77–0020, Revision 3,
dated April 4, 2005.
(2) With an EGT lower harness P/N
CA171–00, with a SN:
(i) Listed in Table 2, Table 4, or Table 5
of CFM56 SB No. CFM56–5B S/B 77–0008,
Revision 3, dated April 4, 2005; or
(ii) Listed in Table 2 or Table 4 of CFM56
SB No. CFM56–5 S/B 77–0020, Revision 3,
dated April 4, 2005.
(3) With an EGT coupling P/N CA172–02
with a SN:
(i) Listed in Table 3, Table 4, or Table 5
of CFM56 Service Bulletin (SB) No. CFM56–
5B S/B 77–0008, Revision 3, dated April 4,
2005, or
(ii) Listed in Table 3 or Table 4 of CFM56
SB No. CFM56–5 S/B 77–0020, Revision 3,
dated April 4, 2005.
(4) These engines are installed on, but not
limited to Airbus Industrie A318, A319,
A320, and A321 airplanes.
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.
(f) If an EGT harness or EGT coupling has
a serial number that is followed by the letter
‘‘W’’, no further action is required for that
part.
(g) For affected EGT harnesses and EGT
couplings identified using paragraph (c) of
this AD, with fewer than 3,000 engine flight
hours-since-installation, do the following:
(1) Replace affected EGT harnesses and
EGT couplings, not being trend monitored,
with serviceable parts within 500 flight hours
after the effective date of this AD; or
(2) After the effective date of this AD:
(i) Review the smooth data EGT trend via
the System for Analysis of Gas Turbine
Engines (SAGE), or equivalent, since the
affected components were first installed on
the current engine.
(ii) Continue this trend monitoring for the
affected EGT harnesses and EGT couplings to
ensure that the system does not show a
minimum of 30 °C downward (i.e. cooler)
indication, or more, without a corresponding
change in other associated engine parameters
such as N1 (LPT rotor speed), N2 (HPT rotor
speed), and fuel flow.
(iii) Provided that there is sufficient, actual
EGT margin to do so, replace the EGT
harnesses and EGT couplings within 100
flight hours after they have been determined
to be defective.
(iv) Continue to monitor the EGT
indications for 3,000 engine flight hours
since the first installation on the current
engine.
Unsafe Condition
(d) This AD results from CFM International
adding subsequently certified engine models,
Terminating Action
(h) Any of the following three conditions
is terminating action for the trend monitoring
Affected ADs
(b) This AD supersedes AD 2003–02–04,
Amendment 39–13020.
requirements specified in paragraphs (g)(2)(i)
through (g)(2)(iv) of this AD:
(1) Replacing an EGT harness and EGT
coupling with a serviceable part, or
(2) Replacing an EGT harness and EGT
coupling with an EGT harness and EGT
coupling that has a letter ‘‘W’’ following the
SN, or
(3) Accumulating 3,000 engine flight hours
on an EGT harness and EGT coupling.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(j) Airworthiness directive No. F–2003–001
R2, dated June 8, 2005, which is from the
Direction Generale de L’Aviation Civile
airworthiness authority for France, also
addresses the subject of this AD.
(k) Contact James Rosa, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7152; fax (781)
238–7199; e-mail: james.rosa@faa.gov for
more information about this AD.
Material Incorporated by Reference
(l) You must use the CFM56 Service
Bulletin Tables specified in the compliance
of this AD, to determine applicability to this
AD. The following Table 1 lists the Service
Bulletins. The Director of the Federal
Register approved the incorporation by
reference of the documents listed in Table 1
of this AD in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact CFM
International, Technical Publications
Department, 1 Neumann Way, Cincinnati,
OH 45215; telephone (513) 552–2800; fax
(513) 552–2816, for a copy of this service
information. You may review copies 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
CFM56 Service Bulletin No.
Page
Revision
Date
CFM56–5B S/B 77–0008 ..................................................................................................................
All ...................
3
April 4, 2005.
All ...................
3
April 4, 2005.
Total Pages: 34
CFM56–5 S/B 77–0020 .....................................................................................................................
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Federal Register / Vol. 72, No. 28 / Monday, February 12, 2007 / Rules and Regulations
Issued in Burlington, Massachusetts, on
January 31, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–2068 Filed 2–9–07; 8:45 am]
Burlington, MA 01803; telephone (781)
238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26570; Directorate
Identifier 2006–NE–39–AD; Amendment 39–
14931; AD 2007–03–20]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Makila 1A and 1A1 Turboshaft
Engines
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)
issued 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:
SUMMARY:
erjones on PRODPC74 with RULES
The back-up mode can be activated by an
electrostatic discharge or by a malfunction of
the collective pitch signal. The two engines
fitted on the same helicopter can therefore be
frozen in this back-up position at 85% N1.
Freezing both engines in the back-up
mode can lead to an inability to
continue safe flight and forced landing.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
March 19, 2007. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD as of
March 19, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
VerDate Aug<31>2005
15:23 Feb 09, 2007
Jkt 211001
6459
received no comments on the NPRM or
on the determination of the cost to the
public.
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S. certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
Conclusion
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 December 19, 2006 (71 FR
75896). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
The control system of the engines covered
by this Airworthiness Directive includes an
electrical back-up mode at 85% N1 (gas
generator speed) activated on the detection of
certain occurrences affecting engine control.
The activation of the back-up mode is
irreversible and freezes the engine at 85%
N1.
An analysis of reported occurrences in
service showed that the back-up mode can be
activated by an electrostatic discharge or by
a malfunction of the collective pitch signal.
The two engines fitted on the same helicopter
can therefore be frozen in this back-up
position at 85% N1.
The present Airworthiness Directive
therefore imposes the application of
modification TU241 on the LPG board of the
Makila 1A and 1A1 ECU, which reduces the
aforementioned risk by changing the
conditions in which the engines switch to
and are maintained in the 85% NG back-up
mode.
Freezing both engines in the back-up
mode can lead to an inability to
continue safe flight and forced landing.
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
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Fmt 4700
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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.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
described in a separate paragraph of the
AD, and take precedence over the
actions copied from the MCAI.
Differences Between This AD and the
Proposed AD
In paragraph (e) of the proposed AD,
published December 19, 2006, we state
‘‘Unless already done, before January
31, 2007, apply the modification TU 241
by replacing the LPG board of the ECU
using Turbomeca Mandatory Service
Bulletin No. 298 73 0241, dated April 5,
2006.’’ Because that compliance date
will have past before this AD becomes
effective, we have changed paragraph (e)
to read, ‘‘Unless already done, within 30
days after the effective date of this AD,
apply the modification TU 241 by
replacing the LPG board of the ECU
using Turbomeca Mandatory Service
Bulletin No. 298 73 0241, dated April 5,
2006.’’
Costs of Compliance
Based on the service information, we
estimate that this AD will affect about
five products of U.S. registry. We also
estimate that it will take about 1.0 workhour per product to comply with this
AD. The average labor rate is $80 per
work-hour. Required parts will cost
about $3,500 per product. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
E:\FR\FM\12FER1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 28 (Monday, February 12, 2007)]
[Rules and Regulations]
[Pages 6457-6459]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-2068]
[[Page 6457]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27112; Directorate Identifier 2001-NE-49-AD;
Amendment 39-14926; AD 2007-03-15]
RIN 2120-AA64
Airworthiness Directives; CFM International CFM56-5 and -5B
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for CFM International CFM56-5 and -5B series turbofan engines.
That AD requires exhaust gas temperature (EGT) harness replacement or
the establishment of an EGT baseline and trend monitoring. That AD also
requires replacement, if necessary, of certain EGT harnesses and EGT
couplings as soon as a slow and continuous EGT drift downward is
noticed after the effective date of that AD. This AD requires the same
actions but for an increased population of affected EGT harnesses. This
AD results from CFM International adding subsequently certified engine
models to the list of engines that could have affected harnesses
installed. We are issuing this AD to prevent unexpected deterioration
of critical rotating engine parts due to higher than desired engine
operating EGTs.
DATES: This AD becomes effective March 19, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of March 19, 2007.
ADDRESSES: You can get the service information identified in this AD
from CFM International, Technical Publications Department, 1 Neumann
Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-
2816.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-7152;
fax (781) 238-7199; e-mail: james.rosa@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to CFM International CFM56-
5 and -5B series turbofan engines. We published the proposed AD in the
Federal Register on June 16, 2006 (71 FR 34852). That action proposed
to require, for an increased population of affected EGT harnesses:
EGT harness replacement or the establishment of an EGT
baseline and trend monitoring; and
Replacement, if necessary, of certain EGT harnesses and
EGT couplings as soon as a slow and continuous EGT drift downward is
noticed after the effective date of that AD.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Docket Number Change
We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2007-27112. The old Docket No. became the
Directorate Identifier, which is 2001-NE-49-AD. This AD might get
logged into the DMS docket, ahead of the previously collected documents
from the old docket file, as we are in the process of sending those
items to the DMS.
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.
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 removing Amendment 39-13020 (68 FR
3171, January 23, 2003) and by adding a new airworthiness directive,
[[Page 6458]]
Amendment 39-14926, to read as follows:
2007-03-15 CFM International: Amendment 39-14926; Docket No. FAA-
2007-27112; Directorate Identifier 2001-NE-49-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
19, 2007.
Affected ADs
(b) This AD supersedes AD 2003-02-04, Amendment 39-13020.
Applicability
(c) This AD applies to CFM International CFM56-5 and -5B series
turbofan engines:
(1) With an exhaust gas temperature (EGT) upper harness part
number (P/N) CA170-00, with a serial number (SN):
(i) Listed in Table 1, Table 4, or Table 5 of CFM56 Service
Bulletin (SB) No. CFM56-5B S/B 77-0008, Revision 3, dated April 4,
2005, or
(ii) Listed in Table 1 or Table 4 of CFM56 SB No. CFM56-5 S/B
77-0020, Revision 3, dated April 4, 2005.
(2) With an EGT lower harness P/N CA171-00, with a SN:
(i) Listed in Table 2, Table 4, or Table 5 of CFM56 SB No.
CFM56-5B S/B 77-0008, Revision 3, dated April 4, 2005; or
(ii) Listed in Table 2 or Table 4 of CFM56 SB No. CFM56-5 S/B
77-0020, Revision 3, dated April 4, 2005.
(3) With an EGT coupling P/N CA172-02 with a SN:
(i) Listed in Table 3, Table 4, or Table 5 of CFM56 Service
Bulletin (SB) No. CFM56-5B S/B 77-0008, Revision 3, dated April 4,
2005, or
(ii) Listed in Table 3 or Table 4 of CFM56 SB No. CFM56-5 S/B
77-0020, Revision 3, dated April 4, 2005.
(4) These engines are installed on, but not limited to Airbus
Industrie A318, A319, A320, and A321 airplanes.
Unsafe Condition
(d) This AD results from CFM International adding subsequently
certified engine models, CFM56-5B3/P1, CFM56-5B3/2P1, CFM56-5B4/P1,
and CFM56-5B4/2P1, to the list of engines that could have affected
harnesses installed, and increasing the population of affected EGT
harnesses. We are issuing this AD to prevent unexpected
deterioration of critical rotating engine parts due to higher than
desired engine operating EGTs.
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.
(f) If an EGT harness or EGT coupling has a serial number that
is followed by the letter ``W'', no further action is required for
that part.
(g) For affected EGT harnesses and EGT couplings identified
using paragraph (c) of this AD, with fewer than 3,000 engine flight
hours-since-installation, do the following:
(1) Replace affected EGT harnesses and EGT couplings, not being
trend monitored, with serviceable parts within 500 flight hours
after the effective date of this AD; or
(2) After the effective date of this AD:
(i) Review the smooth data EGT trend via the System for Analysis
of Gas Turbine Engines (SAGE), or equivalent, since the affected
components were first installed on the current engine.
(ii) Continue this trend monitoring for the affected EGT
harnesses and EGT couplings to ensure that the system does not show
a minimum of 30 [deg]C downward (i.e. cooler) indication, or more,
without a corresponding change in other associated engine parameters
such as N1 (LPT rotor speed), N2 (HPT rotor speed), and fuel flow.
(iii) Provided that there is sufficient, actual EGT margin to do
so, replace the EGT harnesses and EGT couplings within 100 flight
hours after they have been determined to be defective.
(iv) Continue to monitor the EGT indications for 3,000 engine
flight hours since the first installation on the current engine.
Terminating Action
(h) Any of the following three conditions is terminating action
for the trend monitoring requirements specified in paragraphs
(g)(2)(i) through (g)(2)(iv) of this AD:
(1) Replacing an EGT harness and EGT coupling with a serviceable
part, or
(2) Replacing an EGT harness and EGT coupling with an EGT
harness and EGT coupling that has a letter ``W'' following the SN,
or
(3) Accumulating 3,000 engine flight hours on an EGT harness and
EGT coupling.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(j) Airworthiness directive No. F-2003-001 R2, dated June 8,
2005, which is from the Direction Generale de L'Aviation Civile
airworthiness authority for France, also addresses the subject of
this AD.
(k) Contact James Rosa, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; telephone (781) 238-7152; fax
(781) 238-7199; e-mail: james.rosa@faa.gov for more information
about this AD.
Material Incorporated by Reference
(l) You must use the CFM56 Service Bulletin Tables specified in
the compliance of this AD, to determine applicability to this AD.
The following Table 1 lists the Service Bulletins. The Director of
the Federal Register approved the incorporation by reference of the
documents listed in Table 1 of this AD in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact CFM International, Technical
Publications Department, 1 Neumann Way, Cincinnati, OH 45215;
telephone (513) 552-2800; fax (513) 552-2816, for a copy of this
service information. You may review copies 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
----------------------------------------------------------------------------------------------------------------
CFM56 Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
CFM56-5B S/B 77-0008............................ All.................... 3 April 4, 2005.
Total Pages: 34
----------------------------------------------------------------------------------------------------------------
CFM56-5 S/B 77-0020............................. All.................... 3 April 4, 2005.
Total Pages: 16
----------------------------------------------------------------------------------------------------------------
[[Page 6459]]
Issued in Burlington, Massachusetts, on January 31, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-2068 Filed 2-9-07; 8:45 am]
BILLING CODE 4910-13-P
