Airworthiness Directives; General Electric Company (GE) CF6-80C2 Turbofan Engines, 9662-9666 [07-986]
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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations
Actions
Compliance
Procedures
(2) Replace the old engine mount attaching
hardware by doing the following:.
(i) Remove and discard the upper left and
upper right engine mount attaching hardware;
(ii) Cut out and remove the upholstery and
insulation material to allow full metal-tometal contact of the fuselage tubular
frame to the firewall; and
(iii) Install the new upper left and upper
right engine mount attaching hardware
part kits
(3) If you do the actions of paragraph (e)(2) of
this AD before the compliance time specified
for the action in paragraph (e)(1) of this AD,
it terminates the requirement for the action in
paragraph (e)(1) of this AD.
Within the next 100 hours time-in-service
(TIS) after April 9, 2007 (the effective date
of this AD).
Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December
22, 2006.
As of April 9, 2007 (the effective date of this
AD).
Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December
22, 2006.
(f) Compliance will be acceptable if the
above actions are accomplished by following
the procedures described in Mooney
Airplane Company, Inc. Service Bulletin
M20–292, dated September 22, 2006. You
may take ‘‘unless already done’’ credit, and
no further action per this AD is necessary.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Fort Worth Airplane
Certification Office, FAA, ATTN: Andrew
McAnaul, Aerospace Engineer, ASW–150
(c/o MIDO–43), 10100 Reunion Place, Suite
650, San Antonio, Texas 78216; telephone:
(210) 308–3365; fax: (210) 308–3370, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
Related Information
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Material Incorporated by Reference
(i) You must use Mooney Airplane
Company, Inc. Service Bulletin M20–292A,
dated December 22, 2006, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact the Mooney Airplane
Company, Inc., 165 Al Mooney Road North,
Kerrville, TX 78028, telephone: 830–896–
6000, or go to: https://www.mooney.com/
images/pdfs/sb-pdf/m20-292a.pdf.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; 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/
code_of_federal_regulations/ibr_
locations.html.
15:27 Mar 02, 2007
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23871; Directorate
Identifier 2006–NE–01–AD; Amendment 39–
14975; AD 2007–05–14]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2
Turbofan Engines
(h) None.
VerDate Aug<31>2005
Issued in Kansas City, Missouri, on
February 21, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–3575 Filed 3–2–07; 8:45 am]
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF6–80C2 series turbofan engines. This
AD requires replacing certain installed
part number (P/N) and serial number
(SN) cast titanium weld-repaired
forward engine mount platforms and
cast titanium forward mount yokes,
with a forged titanium or a non-welded
cast titanium part. This AD results from
the discovery of cracks, in a weldrepaired area on a forward engine
mount platform and a forward engine
mount yoke, found during a fluorescent
penetrant inspection (FPI). These parts
were weld-repaired during manufacture.
We are issuing this AD to prevent cracks
in the forward engine mount platform
and forward engine mount yoke that
could result in possible separation of
the engine from the airplane.
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This AD becomes effective April
9, 2007.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Company via Lockheed
Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax
(513) 672–8422.
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 Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7176; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80C2 series turbofan
engines. We published the proposed AD
in the Federal Register on December 13,
2006 (71 FR 74873). That action
proposed to require replacing certain
installed part number (P/N) and serial
number (SN) cast titanium weldrepaired forward engine mount
platforms and cast titanium forward
mount yokes, with a forged titanium or
a non-welded cast titanium part.
DATES:
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 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.
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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations
Costs of Compliance
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 have
considered the comments received.
Add Airbus A310 and MD–11 Airplanes
to the Applicability
Commenters from Lufthansa Technik,
KLM Royal Dutch Airlines, Airbus and
Alitalia state that this AD is also
applicable to the engines installed in the
A310 and MD–11 airplanes. We agree.
We inadvertently omitted the Airbus
A310 and MD–11 airplanes from the
Applicability section of the proposed
rule. These airplanes are included in the
Applicability section of the AD.
Commenters from Lufthansa Technik,
KLM Royal Dutch Airlines, Airbus and
Alitalia also state that because the AD
mandates requirements contained in GE
Service Bulletins, CF6–80C2 S/B 72–
1206 and CF6–80C2 S/B 72–1207, the
FAA should reference the service
bulletins in the final rule. We agree. The
service bulletins’ accomplishment
instructions contain information such as
applicable Aircraft Maintenance Manual
sections that would clarify requirements
of the AD. A reference to the service
bulletins is included in the Related
Information Section of the AD.
Location of Weld Repair
Representatives from Lufthansa
Technik and KLM Royal Dutch Airlines
note that paragraph (h) of the
applicability section identifies a weld
repair in a redundant area of the yoke,
but Table 3 identifies the weld repair in
a non-redundant area of the yoke. The
FAA needs to correct this inconsistency
in the final rule. We agree and have
changed the heading of Table 3 to read,
‘‘Weld-Repaired Forward Engine Mount
Yokes Requiring Replacement That
Have a Weld Repair in a Redundant
Area of the Yoke.’’
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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.
15:27 Mar 02, 2007
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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, 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
Reference GE Service Bulletins
VerDate Aug<31>2005
There are 25 engines in service that
contain the substandard forward engine
mount platforms and 59 engines in
service that contain the substandard
forward engine mount yokes. We
estimate that this proposed AD would
affect 84 CF6–80C2 engines installed on
airplanes of U.S. registry. We estimate
that it would take 34 work-hours per
engine to replace the weld-repaired cast
titanium forward engine mount
platforms and the weld-repaired cast
titanium forward engine mount yokes.
The average labor rate is $80 per workhour. Required forward engine mount
parts would cost about $12,168 per
engine. Required forward engine mount
yoke parts would cost about $39,560 per
engine. Based on these figures, we
estimate the total cost of the proposed
AD to U.S. operators to be $2,866,720.
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
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9663
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:
I
2007–05–14 General Electric Company:
Amendment 39–14975. Docket No.
FAA–2006–23871; Directorate Identifier
2006–NE–01–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
General Electric Company (GE) turbofan
engines with cast titanium assembly engine
mount platforms part numbers (P/Ns)
1292M13G06, 1301M28G08, 1459M70G07,
and 1846M24G04 and cast titanium assembly
engine mount yokes P/Ns 9383M43G14 and
9383M43G16 installed.
CF6–80C2A1
CF6–80C2A2
CF6–80C2A3
CF6–80C2A5
CF6–80C2A8
CF6–80C2A5F
CF6–80C2B1
CF6–80C2B2
CF6–80C2B4
CF6–80C2B6
CF6–80C2B1F
CF6–80C2B2F
CF6–80C2B4F
CF6–80C2B5F
CF6–80C2B6F
CF6–80C2B6FA
CF6–80C2B7F
CF6–80C2B8F
CF6–80C2D1F
These engines are installed on, but not
limited to, Boeing 747, Boeing 767, MD–11
and Airbus A300–600 and A310 airplanes.
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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations
Unsafe Condition
(d) This AD results from the discovery of
cracks in a forward engine mount platform
and a forward engine mount yoke found
during fluorescent penetrant inspection (FPI).
We are issuing this AD to prevent cracks in
the forward engine mount platform and
forward engine mount yoke that could result
in possible separation of the engine from 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.
P/N and SN Weld-Repaired Forward Engine
Mount Platforms and Forward Engine Mount
Yokes Requiring Replacement
(f) Table 1 of this AD lists the P/Ns and
serial numbers (SNs) of the weld-repaired
forward engine mount platforms that have a
weld repair in a non-redundant area of the
mount and must be replaced.
TABLE 1.—WELD-REPAIRED FORWARD
ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE
A WELD REPAIR IN A NON-REDUNDANT AREA OF THE MOUNT
P/Ns
1292M13G06 or
1846M24G04
1301M28G08 .....................
TABLE 2.—WELD-REPAIRED FORWARD
ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE
A WELD REPAIR IN A REDUNDANT
AREA OF THE MOUNT—Continued
P/Ns
1459M70G07 .....................
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VerDate Aug<31>2005
TABLE 3.—WELD-REPAIRED FORWARD
ENGINE MOUNT YOKES REQUIRING
REPLACEMENT THAT HAVE A WELD
REPAIR IN A REDUNDANT AREA OF
THE YOKE
P/Ns
WACHH173
WACHH189
WACHH274
WACHH278
WACHH314
WACHH325
WACHH486
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SNs
9383M43G14 .....................
SNs
15:27 Mar 02, 2007
WACAR294
WACAR304
WACAR353
WACAR372
MTXT1282
9383M43G16 .....................
TABLE 2.—WELD-REPAIRED FORWARD
ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE
A WELD REPAIR IN A REDUNDANT
AREA OF THE MOUNT
1292M13G06 or
1846M24G04
P/Ns
(h) Table 3 of this AD lists the P/Ns and
SNs of the weld-repaired forward engine
mount yokes that have a weld repair in a
redundant area of the yoke. Because it is
impossible to detect whether the mount yoke
is operating on the redundant feature, each
of these mount yokes must be replaced. The
compliance time for mounts in this category
can be longer than for the mounts listed in
Table 1 of this AD.
(g) Table 2 of this AD lists the P/Ns and
SNs of the weld-repaired forward engine
mount platforms that have a weld repair in
a redundant area of the mount. Because it is
impossible to detect whether the mount is
operating on the redundant feature, each of
these mounts must be replaced. The
compliance time for mounts in this category
can be longer than for the mounts listed in
Table 1 of this AD.
P/Ns
SNs
1301M28G08 .....................
SNs
WACHH228
WACHH254
WACHH285
WACHH290
WACHH292
WACHH295
WACHH299
WACHH384
WACHH427
WACHH440
WACHH604
WACAR292
WACAR354
TABLE 3.—WELD-REPAIRED FORWARD
ENGINE MOUNT YOKES REQUIRING
REPLACEMENT THAT HAVE A WELD
REPAIR IN A REDUNDANT AREA OF
THE YOKE—Continued
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WACV0394
WACV0405
WACV0406
WACV0477
WACV0498
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WACV0556
WACV0579
WACV0581
WACV0582
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SNs
WACV2511
WACV2695
WACV2707
WACV2881
WACV2899
WACV0511
WACV0515
WACV0518
WACV0540
WACV0542
WACV0571
WACV0689
WACV0721
WACV0727
WACV0730
WACV0786
WACV0816
WACV0954
(i) GE advises that forward engine mount
platform, P/Ns 1292M13G06 and
1846M24G04, are the same, except that P/N
1846M24G04 incorporates a previously
approved field rework. This rework allows
the thrust pin hole in the forward engine
mount platform to be bored out to accept
installation of an oversized thrust pin. GE
cannot identify which SN goes with which P/
N, but all SNs are affected.
Welded Cast Titanium Forward Engine
Mount Platform and Forward Engine Mount
Yoke Removal
(j) If the P/N and SN of the forward engine
mount platform listed in Table 1 and Table
2 and the forward engine mount yoke listed
in Table 3 of this AD are not installed on the
engine, no further action is necessary.
(k) If the P/N and SN of the forward engine
mount platform listed in Table 1 of this AD
is installed on the engine:
(1) Remove the forward engine mount
platform from the engine within 500 cycles
or 6 months, after the effective date of this
AD, whichever occurs first.
(2) Information for removal of the forward
engine mount platform from the engine can
be found in the CF6–80C2 Engine Manual,
72–00–01, Disassembly.
(l) If the P/N and SN of the forward engine
mount platform listed in Table 2 of this AD
is installed on the engine:
(1) Remove the forward engine mount
platform at the next shop visit, or within
4,800 cycles after the effective date of this
AD, whichever occurs first.
(2) Information for removal of the forward
engine mount yoke can be found in the CF6–
80C2 Engine Manual, 72–00–01,
Disassembly.
(m) If the P/N and SN of the forward
engine mount yoke listed in Table 3 of this
AD is installed on the engine:
(1) Remove the forward engine mount yoke
at the next shop visit, or within 4,800 cycles
after the effective date of this AD, whichever
occurs first.
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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations
9665
cast titanium forward engine mount platform
and or the forward engine mount yoke or a
forged titanium forward engine mount
platform or a forged titanium forward engine
mount yoke.
(o) Information for installing the forward
engine mount platform and forward engine
mount yoke can be found in the CF6–80C2
Engine Manual, 72–00–01, Assembly.
(p) Location of the forward engine mount
platform and forward engine mount yoke and
SN are illustrated in the following Figure 1.
(q) After the effective date of this AD, do
not install a weld-repaired, cast forward
engine mount platform or a weld-repaired,
cast forward engine mount yoke in any
engine.
Alternative Methods of Compliance
Related Information
(r) 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.
(s) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7176; fax (781)
VerDate Aug<31>2005
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(2) Information for removal of the forward
engine mount yoke can be found in the CF6–
80C2 Engine Manual, 72–00–01,
Disassembly.
(n) Replace the affected forward engine
mount platform and or the affected forward
engine mount yoke with a non-weld-repaired
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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations
238–7199 for more information about this
AD.
(t) General Electric Company Service
Bulletins CF6–80C2 S/B 72–1206, dated
December 23, 2005, and CF6–80C2 S/B 72–
1207, Revision 01, dated July 05, 2006,
pertain to the subject of this AD.
Issued in Burlington, Massachusetts, on
February 27, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 07–986 Filed 3–2–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26378; Directorate
Identifier 2006–NM–230–AD; Amendment
39–14972; AD 2007–05–11]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B16 (CL–604)
Airplanes and Model CL–600–2B19
(Regional Jet Series 100 & 440)
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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AGENCY:
SUMMARY: The FAA is superseding two
existing airworthiness directives (ADs),
that apply to certain Bombardier Model
CL–600–2B16 (CL–604) airplanes and
Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. These
models may be referred to by their
marketing designations as RJ100, RJ200,
RJ440, CRJ100, CRJ200, CRJ440, and
CL–65. One existing AD requires
replacing the horizontal stabilizer trim
control unit (HSTCU) with a new
HSTCU. The other existing AD requires
revising the airplane flight manual
(AFM) to advise the flightcrew of
procedures to follow in the event of
stabilizer trim runaway, and in the
event of MACH TRIM, STAB TRIM, and
horizontal stabilizer trim malfunctions;
and revising the AFM to require a
review of the location of certain circuit
breakers. That AD also requires doing a
functional check of the stabilizer trim
system and installing circuit breaker
identification collars, and provides an
optional terminating action. This new
AD requires the previously optional
terminating action and requires further
revisions to the AFM. This AD also
requires the removal of certain AFM
revisions. This AD results from reports
VerDate Aug<31>2005
15:27 Mar 02, 2007
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of trim problems including
uncommanded trim, trim in the
opposite direction to that selected, loss
of trim position indication and, in one
case, potential loss of trim disconnect
capability. We are issuing this AD to
prevent these events, which could result
in conditions that vary from reduced
controllability of the airplane to loss of
control of the airplane.
DATES: This AD becomes effective
March 20, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 20, 2007.
On November 14, 2006 (71 FR 63219,
October 30, 2006), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications.
On July 30, 1998 (63 FR 34574, June
25, 1998), the Director of the Federal
Register approved the incorporation by
reference of a certain other publication.
We must receive any comments on
this AD by April 4, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this AD.
You may examine the contents of 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., Room PL–401, on the plaza level
of the Nassif Building, Washington, DC.
This docket number is FAA–2006–
26378; the directorate identifier for this
docket is 2006–NM–230–AD.
FOR FURTHER INFORMATION CONTACT:
Daniel Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
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Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7305; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
On October 13, 2006, the FAA issued
a supplemental notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2006–22–06, amendment
39–14803 (71 FR 63219, October 30,
2006). The existing AD applies to
certain Bombardier Model CL–600–
2B16 (CL–604) airplanes and Model CL–
600–2B19 (Regional Jet Series 100 &
440) airplanes. That supplemental
NPRM was published in the Federal
Register on December 28, 2006 (71 FR
78096). That supplemental NPRM
proposed to retain the requirements of
AD 2006–22–06 and to require the
previously optional terminating action
(installation of a new horizontal
stabilizer trim control unit (HSTCU)).
That supplemental NPRM also proposed
to require, for certain airplanes, reinserting the applicable temporary
revisions of the Emergency and
Abnormal Procedures sections of the
airplane flight manual (AFM) under
certain conditions.
Actions Since Supplemental NPRM
Was Issued
Since we issued that supplemental
NPRM, Bombardier has issued new
temporary revisions (TRs) to the AFMs
as described in a comment submitted by
the National Transportation Safety
Board (NTSB) (see ‘‘Request to Revise
AFM Procedures’’ paragraph below). In
the comment, the NTSB presents data to
indicate that changes to the AFMs are
necessary to address the identified
unsafe condition. We have coordinated
with Transport Canada Civil Aviation
(TCCA) on this issue and concur that
changes to the AFMs are necessary. In
consideration of these new data, we
have determined that the AFMs must be
revised to include the new TRs within
14 days after the effective date of this
AD.
The FAA finds that, with respect to
this additional requirement, since a
situation exists that requires immediate
adoption of this requirement, notice and
time for prior public comment hereon
are impracticable, and good cause exists
for making this amendment effective in
less than 30 days. Therefore, this AD
will include the requirements specified
in the supplemental NPRM (except the
proposed requirement to re-insert TRs to
the AFMs), as well as the certain new
requirements discussed below. The new
requirements include revising the AFMs
to include the new TRs. In addition, we
E:\FR\FM\05MRR1.SGM
05MRR1
]]>Agencies
[Federal Register Volume 72, Number 42 (Monday, March 5, 2007)]
[Rules and Regulations]
[Pages 9662-9666]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-986]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23871; Directorate Identifier 2006-NE-01-AD;
Amendment 39-14975; AD 2007-05-14]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF6-80C2 series turbofan engines. This AD requires replacing certain
installed part number (P/N) and serial number (SN) cast titanium weld-
repaired forward engine mount platforms and cast titanium forward mount
yokes, with a forged titanium or a non-welded cast titanium part. This
AD results from the discovery of cracks, in a weld-repaired area on a
forward engine mount platform and a forward engine mount yoke, found
during a fluorescent penetrant inspection (FPI). These parts were weld-
repaired during manufacture. We are issuing this AD to prevent cracks
in the forward engine mount platform and forward engine mount yoke that
could result in possible separation of the engine from the airplane.
DATES: This AD becomes effective April 9, 2007.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company via Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513)
672-8400, fax (513) 672-8422.
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 Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80C2 series
turbofan engines. We published the proposed AD in the Federal Register
on December 13, 2006 (71 FR 74873). That action proposed to require
replacing certain installed part number (P/N) and serial number (SN)
cast titanium weld-repaired forward engine mount platforms and cast
titanium forward mount yokes, with a forged titanium or a non-welded
cast titanium part.
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 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.
[[Page 9663]]
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 have considered the comments received.
Add Airbus A310 and MD-11 Airplanes to the Applicability
Commenters from Lufthansa Technik, KLM Royal Dutch Airlines, Airbus
and Alitalia state that this AD is also applicable to the engines
installed in the A310 and MD-11 airplanes. We agree. We inadvertently
omitted the Airbus A310 and MD-11 airplanes from the Applicability
section of the proposed rule. These airplanes are included in the
Applicability section of the AD.
Reference GE Service Bulletins
Commenters from Lufthansa Technik, KLM Royal Dutch Airlines, Airbus
and Alitalia also state that because the AD mandates requirements
contained in GE Service Bulletins, CF6-80C2 S/B 72-1206 and CF6-80C2 S/
B 72-1207, the FAA should reference the service bulletins in the final
rule. We agree. The service bulletins' accomplishment instructions
contain information such as applicable Aircraft Maintenance Manual
sections that would clarify requirements of the AD. A reference to the
service bulletins is included in the Related Information Section of the
AD.
Location of Weld Repair
Representatives from Lufthansa Technik and KLM Royal Dutch Airlines
note that paragraph (h) of the applicability section identifies a weld
repair in a redundant area of the yoke, but Table 3 identifies the weld
repair in a non-redundant area of the yoke. The FAA needs to correct
this inconsistency in the final rule. We agree and have changed the
heading of Table 3 to read, ``Weld-Repaired Forward Engine Mount Yokes
Requiring Replacement That Have a Weld Repair in a Redundant Area of
the Yoke.''
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
There are 25 engines in service that contain the substandard
forward engine mount platforms and 59 engines in service that contain
the substandard forward engine mount yokes. We estimate that this
proposed AD would affect 84 CF6-80C2 engines installed on airplanes of
U.S. registry. We estimate that it would take 34 work-hours per engine
to replace the weld-repaired cast titanium forward engine mount
platforms and the weld-repaired cast titanium forward engine mount
yokes. The average labor rate is $80 per work-hour. Required forward
engine mount parts would cost about $12,168 per engine. Required
forward engine mount yoke parts would cost about $39,560 per engine.
Based on these figures, we estimate the total cost of the proposed AD
to U.S. operators to be $2,866,720.
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, 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:
2007-05-14 General Electric Company: Amendment 39-14975. Docket No.
FAA-2006-23871; Directorate Identifier 2006-NE-01-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April 9,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following General Electric Company
(GE) turbofan engines with cast titanium assembly engine mount
platforms part numbers (P/Ns) 1292M13G06, 1301M28G08, 1459M70G07,
and 1846M24G04 and cast titanium assembly engine mount yokes P/Ns
9383M43G14 and 9383M43G16 installed.
CF6-80C2A1
CF6-80C2A2
CF6-80C2A3
CF6-80C2A5
CF6-80C2A8
CF6-80C2A5F
CF6-80C2B1
CF6-80C2B2
CF6-80C2B4
CF6-80C2B6
CF6-80C2B1F
CF6-80C2B2F
CF6-80C2B4F
CF6-80C2B5F
CF6-80C2B6F
CF6-80C2B6FA
CF6-80C2B7F
CF6-80C2B8F
CF6-80C2D1F
These engines are installed on, but not limited to, Boeing 747,
Boeing 767, MD-11 and Airbus A300-600 and A310 airplanes.
[[Page 9664]]
Unsafe Condition
(d) This AD results from the discovery of cracks in a forward
engine mount platform and a forward engine mount yoke found during
fluorescent penetrant inspection (FPI). We are issuing this AD to
prevent cracks in the forward engine mount platform and forward
engine mount yoke that could result in possible separation of the
engine from 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.
P/N and SN Weld-Repaired Forward Engine Mount Platforms and Forward
Engine Mount Yokes Requiring Replacement
(f) Table 1 of this AD lists the P/Ns and serial numbers (SNs)
of the weld-repaired forward engine mount platforms that have a weld
repair in a non-redundant area of the mount and must be replaced.
Table 1.--Weld-Repaired Forward Engine Mount Platforms Requiring
Replacement That Have a Weld Repair in a Non-Redundant Area of the Mount
------------------------------------------------------------------------
P/Ns SNs
------------------------------------------------------------------------
1292M13G06 or 1846M24G04 WACHH228
WACHH254
WACHH285
WACHH290
WACHH292
WACHH295
WACHH299
WACHH384
WACHH427
WACHH440
WACHH604
1301M28G08............................. WACAR292
WACAR354
------------------------------------------------------------------------
(g) Table 2 of this AD lists the P/Ns and SNs of the weld-
repaired forward engine mount platforms that have a weld repair in a
redundant area of the mount. Because it is impossible to detect
whether the mount is operating on the redundant feature, each of
these mounts must be replaced. The compliance time for mounts in
this category can be longer than for the mounts listed in Table 1 of
this AD.
Table 2.--Weld-Repaired Forward Engine Mount Platforms Requiring
Replacement That Have a Weld Repair in a Redundant Area of the Mount
------------------------------------------------------------------------
P/Ns SNs
------------------------------------------------------------------------
1292M13G06 or 1846M24G04 WACHH173
WACHH189
WACHH274
WACHH278
WACHH314
WACHH325
WACHH486
1301M28G08............................. WACAR294
WACAR304
WACAR353
WACAR372
1459M70G07............................. MTXT1282
------------------------------------------------------------------------
(h) Table 3 of this AD lists the P/Ns and SNs of the weld-
repaired forward engine mount yokes that have a weld repair in a
redundant area of the yoke. Because it is impossible to detect
whether the mount yoke is operating on the redundant feature, each
of these mount yokes must be replaced. The compliance time for
mounts in this category can be longer than for the mounts listed in
Table 1 of this AD.
Table 3.--Weld-Repaired Forward Engine Mount Yokes Requiring Replacement
That Have a Weld Repair in a Redundant Area of the Yoke
------------------------------------------------------------------------
P/Ns SNs
------------------------------------------------------------------------
9383M43G14............................. WACV0388
WACV0394
WACV0405
WACV0406
WACV0477
WACV0498
WACV0529
WACV0556
WACV0579
WACV0581
WACV0582
WACV0600
WACV0605
WACV0617
WACV0625
WACV0627
WACV0633
WACV0645
WACV0683
WACV0703
WACV0733
WACV0737
WACV0759
WACV0775
WACV0791
WACV0799
WACV0875
WACV0883
WACV0885
WACV0909
WACV1097
WACV1615
WACV1713
WACV1753
WACV1797
WACV1867
WACV1987
WACV2131
WACV2159
WACV2185
WACV2343
WACV2511
WACV2695
WACV2707
WACV2881
WACV2899
9383M43G16............................. WACV0511
WACV0515
WACV0518
WACV0540
WACV0542
WACV0571
WACV0689
WACV0721
WACV0727
WACV0730
WACV0786
WACV0816
WACV0954
------------------------------------------------------------------------
(i) GE advises that forward engine mount platform, P/Ns
1292M13G06 and 1846M24G04, are the same, except that P/N 1846M24G04
incorporates a previously approved field rework. This rework allows
the thrust pin hole in the forward engine mount platform to be bored
out to accept installation of an oversized thrust pin. GE cannot
identify which SN goes with which P/N, but all SNs are affected.
Welded Cast Titanium Forward Engine Mount Platform and Forward Engine
Mount Yoke Removal
(j) If the P/N and SN of the forward engine mount platform
listed in Table 1 and Table 2 and the forward engine mount yoke
listed in Table 3 of this AD are not installed on the engine, no
further action is necessary.
(k) If the P/N and SN of the forward engine mount platform
listed in Table 1 of this AD is installed on the engine:
(1) Remove the forward engine mount platform from the engine
within 500 cycles or 6 months, after the effective date of this AD,
whichever occurs first.
(2) Information for removal of the forward engine mount platform
from the engine can be found in the CF6-80C2 Engine Manual, 72-00-
01, Disassembly.
(l) If the P/N and SN of the forward engine mount platform
listed in Table 2 of this AD is installed on the engine:
(1) Remove the forward engine mount platform at the next shop
visit, or within 4,800 cycles after the effective date of this AD,
whichever occurs first.
(2) Information for removal of the forward engine mount yoke can
be found in the CF6-80C2 Engine Manual, 72-00-01, Disassembly.
(m) If the P/N and SN of the forward engine mount yoke listed in
Table 3 of this AD is installed on the engine:
(1) Remove the forward engine mount yoke at the next shop visit,
or within 4,800 cycles after the effective date of this AD,
whichever occurs first.
[[Page 9665]]
(2) Information for removal of the forward engine mount yoke can
be found in the CF6-80C2 Engine Manual, 72-00-01, Disassembly.
(n) Replace the affected forward engine mount platform and or
the affected forward engine mount yoke with a non-weld-repaired cast
titanium forward engine mount platform and or the forward engine
mount yoke or a forged titanium forward engine mount platform or a
forged titanium forward engine mount yoke.
(o) Information for installing the forward engine mount platform
and forward engine mount yoke can be found in the CF6-80C2 Engine
Manual, 72-00-01, Assembly.
(p) Location of the forward engine mount platform and forward
engine mount yoke and SN are illustrated in the following Figure 1.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR05MR07.000
(q) After the effective date of this AD, do not install a weld-
repaired, cast forward engine mount platform or a weld-repaired,
cast forward engine mount yoke in any engine.
Alternative Methods of Compliance
(r) 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
(s) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7176; fax (781)
[[Page 9666]]
238-7199 for more information about this AD.
(t) General Electric Company Service Bulletins CF6-80C2 S/B 72-
1206, dated December 23, 2005, and CF6-80C2 S/B 72-1207, Revision
01, dated July 05, 2006, pertain to the subject of this AD.
Issued in Burlington, Massachusetts, on February 27, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 07-986 Filed 3-2-07; 8:45 am]
BILLING CODE 4910-13-P
