[Federal Register: March 5, 2007 (Volume 72, Number 42)]
[Rules and Regulations]
[Page 9662-9666]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05mr07-7]
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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.
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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 http://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.
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[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]
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