[Federal Register Volume 75, Number 110 (Wednesday, June 9, 2010)]
[Rules and Regulations]
[Pages 32649-32651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-13873]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 75, No. 110 / Wednesday, June 9, 2010 / Rules
and Regulations
[[Page 32649]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0068; Directorate Identifier 2010-NE-05-AD;
Amendment 39-16331; AD 2010-12-10]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-45 and
CF6-50 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CF6-45 and CF6-50 series
turbofan engines with certain low-pressure turbine (LPT) rotor stage 3
disks installed. That AD required initial and repetitive borescope
inspections of the high-pressure turbine (HPT) rotor stage 1 and stage
2 blades for wear and damage, including excessive airfoil material
loss. That AD also required fluorescent penetrant inspection (FPI) of
the LPT rotor stage 3 disk under certain conditions and removal of the
disk from service before further flight if found cracked. This ad
requires the same inspections at reduced intervals and additional
borescope inspections. This AD also requires repetitive exhaust gas
temperature (EGT) system checks. This AD results from reports received
of two additional LPT rotor stage 3 disk events. We are issuing this AD
to prevent critical life-limited rotating engine part failure, which
could result in an uncontained engine failure and damage to the
airplane.
DATES: Effective June 24, 2010.
We must receive any comments on this AD by August 9, 2010.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
FOR FURTHER INFORMATION CONTACT: Christopher J. Richards, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: [email protected]; phone: (781) 238-7133; fax: (781)
238-7199.
SUPPLEMENTARY INFORMATION: The FAA amends 14 CFR part 39 by superseding
AD 2010-06-15, Amendment 39-16240 (75 FR 12661, March 17, 2010). That
AD required initial and repetitive borescope inspections of the HPT
rotor stage 1 and stage 2 blades for wear and damage, including
excessive airfoil material loss. That AD also required FPI of the LPT
rotor stage 3 disk under certain conditions and removal of the disk
from service before further flight if found cracked. That AD was the
result of three reports of uncontained failures of LPT rotor stage 3
disks and eight reports of cracked LPT rotor stage 3 disks found during
shop visit inspections. That condition, if not corrected, could result
in an uncontained engine failure and damage to the airplane.
Actions Since AD 2010-06-15 Was Issued
Since AD 2010-06-15 was issued, we received reports of two
additional LPT rotor stage 3 disk events, bringing the total number of
events to five. Additionally, the National Transportation Safety Board
issued Safety Recommendations A-10-98 through A-10-101. These
recommendations include performing a borescope inspection of the HPT
rotor blades more frequently than was originally required in AD 2010-
06-15.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other GE CF6-45 and CF6-50 series turbofan engines of the
same type design. For that reason, we are issuing this AD to prevent
critical life-limited rotating engine part failure, which could result
in an uncontained engine failure and damage to the airplane. This AD
requires initial and repetitive borescope inspections of the HPT rotor
stage 1 and stage 2 blades. This AD also requires additional borescope
inspections and FPI of the LPT rotor stage 3 disk, depending on the
results of the borescope inspection. This AD also requires repetitive
EGT system checks.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2010-0068; Directorate
Identifier 2010-NE-05-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the rule that might suggest a need
to modify it.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of the
Web site, anyone can find and read the comments in any
[[Page 32650]]
of our dockets, including, if provided, 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).
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (phone: (800) 647-5527) is the same as the
Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
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 the 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
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16240 (75 FR
12661, March 17, 2010), and by adding a new airworthiness directive,
Amendment 39-16331, to read as follows:
2010-12-10 General Electric Company: Amendment 39-16331. Docket No.
FAA-2010-0068; Directorate Identifier 2010-NE-05-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 24,
2010.
Affected ADs
(b) This AD supersedes AD 2010-06-15, Amendment 39-16240.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-45A,
CF6-45A2, CF6-50A, CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B,
CF6-50C2D, CF6-50C2-F, CF6-50C2-R, CF6-50E, CF6-50E1, and CF6-50E2
series turbofan engines, with any of the following low-pressure
turbine (LPT) rotor stage 3 disks installed:
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----------------------------------------------------------------------------------------------------------------
9061M23P06 9061M23P07 9061M23P08 9061M23P09 9224M75P01
9061M23P10 1473M90P01 1473M90P02 1473M90P03 1473M90P04
9061M23P12 9061M23P14 9061M23P15 9061M23P16 1479M75P01
1479M75P02 1479M75P03 1479M75P04 1479M75P05 1479M75P06
1479M75P07 1479M75P08 1479M75P09 1479M75P11 1479M75P13
1479M75P14 N/A N/A N/A N/A
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These engines are installed on, but not limited to, Boeing 747-
200/-300, DC-10, MD-10, and KC-10 aircraft, and Airbus A300 series
aircraft.
Unsafe Condition
(d) This AD results from reports received of two additional LPT
rotor stage 3 disk events. We are issuing this AD to prevent
critical life-limited rotating engine part failure, which could
result in an uncontained engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Borescope Inspections of High-Pressure Turbine (HPT) Rotor Stage 1 and
Stage 2 Blades
(f) Borescope-inspect the HPT rotor stage 1 and stage 2 blades
from the forward and aft directions within 10 cycles from the
effective date of this AD. You can find further guidance about
borescoping in Table 2 of this AD.
(g) Thereafter, borescope-inspect the HPT rotor stage 1 and
stage 2 blades from the forward and aft directions within every 75
cycles-since-last-inspection (CSLI). You can find further guidance
about borescoping in Table 2 of this AD.
Additional Borescope Inspections
(h) Borescope-inspect the HPT rotor stage 1 and stage 2 blades
from the forward and aft directions within the cycle limits after
the engine has experienced the events specified in Table 1 of this
AD. You can find further guidance about borescoping in Table 2 of
this AD.
Table 1--Additional Borescope Inspection Criteria
------------------------------------------------------------------------
If the engine has experienced: Then borescope inspect:
------------------------------------------------------------------------
(1) An exhaust gas temperature (EGT) above Within 10 cycles.
redline.
[[Page 32651]]
(2) A shift in the smoothed EGT trending Within 10 cycles.
data that exceeds 18[deg] F (10[deg] C),
but is less than or equal to 36[deg] F
(20[deg] C).
(3) A shift in the smoothed EGT trending Before further flight.
data that exceeds 36[deg] F (20[deg] C).
(4) A flightcrew reported vibration Within 10 cycles from the
determined to be caused by the high- report.
pressure rotor (N2).
------------------------------------------------------------------------
Actions Required for Engines With Damaged HPT Rotor Blades
(i) Remove the engine before further flight if the engine fails
the borescope inspection in paragraph (f), (g), or (h) of this AD.
(j) Before returning the engine to service, fluorescent
penetrant inspect the inner diameter surface forward cone body
(forward spacer arm) of the LPT rotor stage 3 disk. If a crack is
found or if a circumferential band of fluorescence appears,
permanently remove the disk from service.
EGT System Checks
(k) Inspect the turbine midframe (TMF) liner for clocking and
subsequent damage to the EGT probes, within 50 cycles from the
effective date of this AD or before accumulating 750 CSLI of the TMF
liner for clocking, whichever occurs later. You can find further
guidance about TMF liner inspections in Table 2 of this AD.
(l) Thereafter, inspect the TMF liner for clocking and
subsequent damage to the EGT probes within every 750 CSLI. You can
find further guidance about TMF liner inspections in Table 2 of this
AD.
(m) If the engine shows TMF liner clocking resulting in wear
through 100% of the wall thickness of the thermocouple guide sleeve,
remove the engine and repair the TMF and any damage to the EGT
probes before further flight. You can find further guidance about
TMF liner inspections in Table 2 of this AD.
(n) Check the resistance of the EGT system within 50 cycles from
the effective date of this AD or before accumulating 750 cycles-
since-the-last-resistance check of the EGT system, whichever occurs
later. You can find further guidance about the EGT resistance check
in Table 2 of this AD.
(o) Thereafter, check the resistance of the EGT system within
every 750 CSLI. You can find further guidance about EGT resistance
checks in Table 2 of this AD.
(p) Repair or replace any EGT system component that fails this
check, before further flight. You can find further guidance about
the EGT resistance check in Table 2 of this AD.
Definitions
(q) For the purposes of this AD, an EGT above redline is a
confirmed over temperature indication that is not a result of EGT
system error. You can find further guidance about troubleshooting
EGT above redline in Table 2 of this AD.
(r) For the purposes of this AD, a shift in the smoothed EGT
trending data is a shift in a rolling average of EGT that can be
confirmed by a corresponding shift in the trending of fuel flow or
fan speed/core speed relationship. You can find further guidance
about evaluating EGT trend data in GE Company Service Rep Tip 373
``Guidelines For Parameter Trend Monitoring.''
Table 2--AMM References for Further Guidance
----------------------------------------------------------------------------------------------------------------
Boeing 747/CF6-50/- Boeing DC-10/CF6- Boeing MD-10/CF6- Airbus A300/CF6-50
Engine inspections 45 AMM ATA 50 AMM ATA 50 AMM ATA AMM ATA
----------------------------------------------------------------------------------------------------------------
Borescope Inspection of HPT 72-00-00, 601..... 72-53-00.......... 72-53-00.......... 72-53-00.
Rotor Stage 1 and Stage 2
Blades.
Exceeded EGT Limit.............. 72-00-00, 601..... 72-00-00, 601..... 72-00-00, 6-1..... 72-00-00, 601.
EGT Resistance Check............ 77-21-00, 501..... 77-21-00.......... 77-21-01.......... 77-21-00.
TMF Liner Clocking.............. 72-00-00, 601, and 72-54-00.......... 72-54-00 and 77-21- 72-54-00.
72-52-00. 01.
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Previous Credit
(s) A borescope inspection performed before the effective date
of this AD using AD 2010-06-15 and within the last 75 cycles,
satisfies the initial borescope inspection requirement in paragraph
(f) of this AD.
Alternative Methods of Compliance
(t) Alternative methods of compliance previously approved for AD
2010-06-15, are not approved for this AD.
(u) 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
(v) Contact Christopher J. Richards, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; phone: (781) 238-7133; fax: (781)
238-7199, for more information about this AD.
Material Incorporated by Reference
(w) None.
Issued in Burlington, Massachusetts, on June 4, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-13873 Filed 6-7-10; 11:15 am]
BILLING CODE 4910-13-P