Airworthiness Directives; General Electric Company (GE) CF6-80C2 Turbofan Engines, 74873-74878 [06-9674]
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Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules
Questions/comments for the
industry
Field name
FDIC field description
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Customer Suffix: The suffix of the individual/ personal customer—i.e.
Jr., Sr., III, etc.
Customer Company Name: The company name of the business customer.
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BILLING CODE 6714–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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 weldrepaired during manufacture. We are
proposing 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: We must receive any comments
on this proposed AD by January 12,
2007.
Use one of the following
addresses to comment on this proposed
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–
0001.
• 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.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
ADDRESSES:
14 CFR Part 39
[Docket No. FAA–2006–23871; Directorate
Identifier 2006–NE–01–AD]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for GE
CF6–80C2 series turbofan engines. This
proposed AD would 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. This
proposed AD results from the discovery
16:44 Dec 12, 2006
How are business customers reflected
in
your
customer
records? Are there multiple
name/address fields?
Address Line 1: Two lines (Fields 13 & 14) are provided to enter the
street, PO Box, suite number, etc. of the address.
Address Line 2: Additional address field.
City: Enter the city associated with the mailing address of the customer.
State: Enter the state abbreviation associated with the mailing address of the customer.
ZIP: This field allows for the ZIP+ 4 Code associated with the mailing address of the customer.
Country: This field should identify the country associated with the
mailing address. Provide the name of the country or the standard
country code.
Customer Birth Date: The birth date on record for the customer.
Must be entered in MMDDYYYY format.
Customer Telephone Number: The telephone number on record for
the customer.
Customer Email Address: The e-mail address on record for the customer.
By order of the Board of Directors.
Dated at Washington, DC, this 5th day of
December, 2006.
Federal Deposit Insurance Corporation.
Robert E. Feldman,
Executive Secretary.
[FR Doc. E6–21143 Filed 12–12–06; 8:45 am]
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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:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2006–23871; Directorate Identifier
2006–NE–01–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DOT
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
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Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules
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 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.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration proposes to
amend 14 CFR part 39 as follows:
FAA’s Determination and Requirements
of the Proposed AD
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.
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require replacing certain
installed P/N and 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.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received, and any final disposition in
person at the DOT 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
Docket Management Facility receives
them.
Discussion
jlentini on PROD1PC65 with PROPOSAL
During an FPI inspection of the
forward engine mount platform and
forward engine mount yoke, an air
carrier found crack indications in the
forward engine mount platform and
yoke, and reported the findings to GE.
An audit of GE’s manufacturing records
revealed 25 cast titanium forward
engine mount platforms, including the
one found cracked, and 59 cast titanium
forward engine mount yokes, had been
weld-repaired at manufacture in either
the pylon thrust pin hole or in the pylon
attach bolt-hole region. Therefore, 25
cast titanium forward engine mount
platforms and 59 cast titanium forward
engine mount yokes would be affected
by this proposed AD. Although the weld
repairs were an approved GE practice at
the time, it has since been determined
that the welding results in cracking in
critical areas of the forward engine
mount platforms and yokes. This
condition, if not corrected, could result
in possible separation of the engine
from the airplane.
CF6–80C2A1
CF6–80C2A2
CF6–80C2A3
CF6–80C2A5
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.................................
.................................
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16:44 Dec 12, 2006
CF6–80C2A8 ................................
CF6–80C2A5F ..............................
CF6–80C2B1 ................................
CF6–80C2B2 ................................
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
General Electric Company: Docket No. FAA–
2006–23871; Directorate Identifier 2006–
NE–01–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
January 12, 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.
CF6–80C2B4 ................................
CF6–80C2B6 ................................
CF6–80C2B1F ..............................
CF6–80C2B2F ..............................
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CF6–80C2B4F
CF6–80C2B5F
CF6–80C2B6F
CF6–80C2B6FA
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These engines are installed on, but not
limited to, Boeing 747, Boeing 767, and
Airbus A300–600 airplanes.
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
WACHH228
WACHH254
WACHH285
WACHH290
WACHH292
WACHH295
WACHH299
WACHH384
WACHH427
WACHH440
WACHH604
WACAR292
WACAR354
P/Ns
1301M28G08 ............................
1301M28G08 ............................
WACHH278
WACHH314
WACHH325
WACHH486
WACAR294
WACAR304
WACAR353
WACAR372
MTXT1282
1459M70G07 ............................
9383M43G16 ............................
TABLE 3.—WELD-REPAIRED FORWARD
ENGINE MOUNT YOKES REQUIRING
REPLACEMENT THAT HAVE A WELD
REPAIR IN A NON-REDUNDANT AREA
OF THE YOKE
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
jlentini on PROD1PC65 with PROPOSAL
(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
SNs
1292M13G06 or 1846M24G04
WACHH173
WACHH189
WACHH274
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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.
P/Ns
P/Ns
TABLE 3.—WELD-REPAIRED FORWARD
ENGINE MOUNT YOKES REQUIRING
REPLACEMENT THAT HAVE A WELD
REPAIR IN A NON-REDUNDANT AREA
OF THE YOKE—Continued
SNs
SNs
1292M13G06 or 1846M24G04
TABLE 2.—WELD-REPAIRED FORWARD
ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE
A WELD REPAIR IN A REDUNDANT
AREA OF THE MOUNT—Continued
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SNs
WACV2131
WACV2159
WACV2185
WACV2343
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:
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jlentini on PROD1PC65 with PROPOSAL
(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.
(2) Information for removal of the forward
engine mount yoke can be found in the CF6–
80C2 Engine Manual, 72–00–01,
Disassembly.
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(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.
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(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
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(q) After the effective date of this AD, do
not install a weld-repaired, cast forward
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engine mount platform or a weld-repaired,
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jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules
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Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules
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.
Issued in Burlington, Massachusetts, on
December 7, 2006.
Robert Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–9674 Filed 12–12–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20856; Directorate
Identifier 2004–NE–25–AD]
• 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–
0001.
• 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 MT-Propeller USA, Inc., 1180
Airport Terminal Drive, Deland, FL
32724; telephone (386) 736–7762, fax
(386) 736–7696 or visit https://www.mtpropeller.com for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Airworthiness Directives; MT-Propeller
Entwicklung GmbH Propellers
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7158, fax (781) 238–7170.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
AGENCY:
The FAA proposes to
supersede an existing airworthiness
directive (AD) for certain MT-Propeller
Entwicklung GmbH variable pitch and
fixed pitch propellers manufactured
before 1995 which had not been
overhauled since April 1994. That AD
currently requires overhauling the
propeller blades and performing initial
and repetitive visual inspections of
affected propeller blades. That AD also
requires removing all propeller blades
from service with damaged erosion
sheath bonding or loose erosion sheaths
and installing any missing or damaged
polyurethane protective strips. This
proposed AD would require the same
actions. This proposed AD results from
the need to clarify the population of
affected propellers previously listed in
AD 2006–05–05. We are proposing this
AD to prevent erosion sheath separation
leading to damage of the airplane.
DATES: We must receive any comments
on this proposed AD by February 12,
2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
jlentini on PROD1PC65 with PROPOSAL
SUMMARY:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20856; Directorate Identifier
2004–NE–25–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DMS
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
PO 00000
Frm 00053
Fmt 4702
Sfmt 4702
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and any final disposition in
person at the DMS 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.
Discussion
On February 24, 2006, we issued AD
2006–05–05, Amendment 39–14502 (71
FR 11151, March 6, 2006). That AD
requires overhaul of models MT, MTV–
1, MTV–2, MTV–3, MTV–5, MTV–6,
MTV–7, MTV–9, MTV–10, MTV–11,
MTV–12, MTV–14, MTV–15, MTV–17,
MTV–18, MTV–20, MTV–21, MTV–22,
MTV–24, and MTV–25 propellers with
serial numbers (SNs) below 95000,
which had not been overhauled since
April 1994, within 30 days after the
effective date of the AD. That action also
required performing initial and
repetitive visual inspections of those
propeller blades. That action also
required removing all propeller blades
from service with damaged erosion
sheath bonding or loose erosion sheaths
and to install any missing or damaged
polyurethane protective strips. The
European Aviation Safety Agency
(EASA), which is the airworthiness
authority for the European Union,
notified us that an unsafe condition may
exist on certain MT-Propeller
Entwicklung GmbH propellers.
Actions Since AD 2006–05–05 Was
Issued
Since AD 2006–05–05 was issued,
MT-Propeller Entwicklung GmbH
Propellers and EASA have clarified the
population of affected propellers. AD
2006–05–05 described the affected
propellers as variable pitch and fixed
pitch propellers with serial numbers
(SNs) below 95000. Because propellers
with SNs starting with 00, 01, 02, 03, 04,
05, and 06, were manufactured in the
years 2000, 2001, 2002, 2003, 2004,
2005, and 2006 respectively, some
operators are confused as to whether
their propeller SN is part of the affected
population. For example, propeller SN
00246, manufactured in 2000, would
appear to be part of the affected
population because the number is below
95000. For clarification, we are
proposing to identify the affected
population as variable pitch and fixed
pitch propellers manufactured before
E:\FR\FM\13DEP1.SGM
13DEP1
]]>Agencies
[Federal Register Volume 71, Number 239 (Wednesday, December 13, 2006)]
[Proposed Rules]
[Pages 74873-74878]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-9674]
=======================================================================
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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]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for GE CF6-80C2 series turbofan engines. This proposed AD would 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. This proposed 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 proposing 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: We must receive any comments on this proposed AD by January 12,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed 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 20590-0001.
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.
You may examine the comments on this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
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:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-23871;
Directorate Identifier 2006-NE-01-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DOT Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
[[Page 74874]]
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received, and any final disposition in person at the DOT 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 Docket Management Facility receives
them.
Discussion
During an FPI inspection of the forward engine mount platform and
forward engine mount yoke, an air carrier found crack indications in
the forward engine mount platform and yoke, and reported the findings
to GE. An audit of GE's manufacturing records revealed 25 cast titanium
forward engine mount platforms, including the one found cracked, and 59
cast titanium forward engine mount yokes, had been weld-repaired at
manufacture in either the pylon thrust pin hole or in the pylon attach
bolt-hole region. Therefore, 25 cast titanium forward engine mount
platforms and 59 cast titanium forward engine mount yokes would be
affected by this proposed AD. Although the weld repairs were an
approved GE practice at the time, it has since been determined that the
welding results in cracking in critical areas of the forward engine
mount platforms and yokes. This condition, if not corrected, could
result in possible separation of the engine from the airplane.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
replacing certain installed P/N and 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.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 14 CFR part 39 as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
General Electric Company: Docket No. FAA-2006-23871; Directorate
Identifier 2006-NE-01-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 12,
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........................... CF6-80C2A8............. CF6-80C2B4............. CF6-80C2B4F
CF6-80C2A2........................... CF6-80C2A5F............ CF6-80C2B6............. CF6-80C2B5F
CF6-80C2A3........................... CF6-80C2B1............. CF6-80C2B1F............ CF6-80C2B6F
CF6-80C2A5........................... CF6-80C2B2............. CF6-80C2B2F............ CF6-80C2B6FA
----------------------------------------------------------------------------------------------------------------
[[Page 74875]]
These engines are installed on, but not limited to, Boeing 747,
Boeing 767, and Airbus A300-600 airplanes.
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 Non-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:
[[Page 74876]]
(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.
(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
[[Page 74877]]
[GRAPHIC] [TIFF OMITTED] TP13DE06.002
BILLING CODE 4910-13-C
(q) After the effective date of this AD, do not install a weld-
repaired, cast forward engine mount platform or a weld-repaired,
[[Page 74878]]
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.
Issued in Burlington, Massachusetts, on December 7, 2006.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 06-9674 Filed 12-12-06; 8:45 am]
BILLING CODE 4910-13-P
