[Federal Register: November 2, 2005 (Volume 70, Number 211)]
[Proposed Rules]
[Page 66302-66305]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02no05-24]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 92-ANE-34-AD]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc., (Formerly
AlliedSignal, Inc. and Textron Lycoming) ALF502L Series and ALF502R
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD), AD 95-04-11, for Honeywell International Inc.,
(formerly AlliedSignal, Inc. and Textron Lycoming) ALF502L series and
ALF502R series turbofan engines. That AD currently establishes stress
rupture retirement life limits for certain third stage turbine discs
used in conjunction with certain third stage turbine nozzles. This
proposed AD would bring requirements forward and unchanged, from the
previous AD for ALF502R series turbofan engines. Also, this proposed AD
would establish new reduced stress rupture retirement life limits for
certain part numbers (P/Ns) of third stage turbine disc and shaft
assemblies installed in ALF502L series turbofan engines. This proposed
AD would also require removing those same parts from service using a
drawdown schedule. This proposed AD results from a report of failure of
a third stage turbine disc and shaft assembly, leading to turbine blade
release and separation of the exhaust nozzle. We are proposing this AD
to prevent total loss of engine power, in-flight engine shutdown,
release of turbine blades, separation of the exhaust nozzle, and
possible damage to the airplane.
DATES: We must receive any comments on this proposed AD by January 3,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 92-ANE-34-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
Contact Honeywell Engines, Systems & Services, Customer Support
Center, M/S 26-06/2102-323, P.O. Box 29003, Phoenix, AZ 85038-9003;
telephone (800) 601-3099, for the service information identified in
this proposed AD.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone:
(562) 627-5245, fax: (562) 627-5210.
SUPPLEMENTARY INFORMATION:
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 ``AD Docket No. 92-ANE-34-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by
[[Page 66303]]
the closing date and may amend the proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On March 2, 1995, we issued AD 95-04-11, Amendment 39-9163 (60 FR
11621, April 3, 1995), applicable to ALF502L series and ALF502R series
turbofan engines. That AD established stress rupture retirement life
limits for certain third stage turbine discs used in conjunction with
certain third stage turbine nozzles. That AD resulted from introduction
of an improved design third stage turbine nozzle, and a new reduced
stress rupture retirement life limit for certain third stage turbine
discs on the ALF502L series engines. That condition, if not corrected,
could result in total loss of engine power, in-flight engine shutdown,
and possible damage to the airplane.
Actions Since AD 95-04-11 Was Issued
Since we issued that AD, we received a report of a third stage
turbine disc and shaft assembly failure in an ALF502L-2C engine. The
rim of the disc ruptured during airplane climb, resulting in release of
turbine blades and separation of the exhaust nozzle. Honeywell
International Inc. has also cited several other separation incidents of
third stage turbine blades, resulting in airplane and engine damage.
The third stage turbine disc and shaft assemblies involved in these
events were all of the Honeywell Pre SB No. ALF502L 72-232
configuration.
Relevant Service Information
We have reviewed and approved the technical contents of Honeywell
International Service Bulletin (SB) No. ALF502 72-0004, Revision 17,
dated January 16, 2005. That SB establishes new reduced service life
limits for third stage turbine disc and shaft assemblies installed in
ALF502L series turbofan engines that have operated in the Pre SB No.
ALF502L 72-232 configuration. That SB also describes procedures for
calculating the remaining service life of certain third stage turbine
disc and shaft assemblies that have operated in Pre and Post SB No.
ALF502L 72-232 configurations.
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:
Bringing requirements forward and unchanged from AD 95-04-
11 for ALF502R series turbofan engines; and
For ALF502L series turbofan engines, establishing new
reduced service life limits for third stage turbine disc and shaft
assemblies, P/N 2-143-030-05; P/N 2-143-030-08; P/N 2-143-030-14; P/N
2-143-030-R21; P/N 2-143-030-22; and P/N 2-143-030-23, that have
operated in the Honeywell Pre SB No. ALF502L 72-232 configuration; and
Removing those same parts from service using a drawdown
schedule.
Limiting the special flight permits for this AD by
allowing a onetime special flight if the disc life limit has been
reached.
The proposed AD would require that you calculate the remaining service
life of certain third stage turbine disc and shaft assemblies using the
service information described previously.
Costs of Compliance
There are about 180 Honeywell International, Inc. ALF502L, ALF502L-
2, ALF502L-2A, ALF502L-2C, ALF502L-3, and ALF502R series turbofan
engines of the affected design in the worldwide fleet. We estimate the
proposed AD would affect 170 engines installed on airplanes of U.S.
registry. We also estimate that it would take about 14 work hours per
engine to perform the proposed actions, and that the average labor rate
is $65 per work hour. The prorated cost of a replacement third stage
turbine disc and shaft assembly is estimated to be $40,000. Based on
these figures, we estimate the total labor cost of the proposed AD on
U.S. operators to be $6,954,700.
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 summary of the costs to comply with this proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 92-ANE-34-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, 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 removing Amendment 39-9163 (60 FR
11621, April 3, 1995) and by adding a new airworthiness directive to
read as follows:
Honeywell International Inc. (formerly AlliedSignal, Inc. and
Textron Lycoming): Docket No. 92-ANE-34-AD.
[[Page 66304]]
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 3,
2006.
Affected ADs
(b) This AD supersedes AD 95-04-11, Amendment 39-9163.
Applicability
(c) This AD applies to Honeywell International Inc., (formerly
AlliedSignal, Inc. and Textron Lycoming) ALF502L, ALF502L-2,
ALF502L-2A, ALF502L-2C, and ALF502L-3 series turbofan engines with
third stage turbine disc and shaft assemblies that have operated in
the Honeywell Pre SB No. ALF502L 72-232 configuration. This AD also
applies to ALF502R series engines. These engines are installed on,
but not limited to, BAe Systems AVRO 146 and Bombardier (Canadair)
CL600-1A11 series airplanes.
Unsafe Condition
(d) This AD results from a report of failure of a third stage
turbine disc and shaft assembly, leading to turbine blade release
and separation of the exhaust nozzle. We are issuing this AD to
prevent total loss of engine power, in-flight engine shutdown,
release of turbine blades, separation of the exhaust nozzle, and
possible 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.
ALF502L Series Turbofan Engines
Determination of Third Stage Turbine Disc and Shaft Assembly
Drawdown Schedule
(f) For ALF502L series turbofan engines, determine if the third
stage turbine disc and shaft assembly is currently operating in the
Pre SB No. ALF502L 72-232 configuration as follows:
(1) If third stage turbine nozzle assembly, part number (P/N) 2-
141-120R56/-57 is installed, then Honeywell SB No. ALF502L 72-232
has been complied with. Proceed to the drawdown schedule in
paragraph (h) of this AD.
(2) If any other third stage turbine nozzle assembly is
installed, then the engine is in the Pre SB No. ALF502L 72-232
configuration. Proceed to the drawdown schedule in paragraph (g) of
this AD.
Drawdown Schedule for Third Stage Turbine Disc and Shaft Assemblies
That Are Operating in the Pre SB No. ALF502L 72-232 Configuration
(g) For ALF502L series turbofan engines, use the drawdown
schedule described in the following Table 1, and replace with
serviceable parts:
Table 1.--Drawdown Schedule for Third Stage Turbine Disc and Shaft
Assemblies In Pre SB ALF502L 72-232 Configuration
------------------------------------------------------------------------
If hours-in-service
For third stage turbine disc (HIS) on the
and shaft assembly P/Ns effective date of Then remove
this AD are
------------------------------------------------------------------------
2-143-030-05................ (1) 5,200 or more Within 50 additional
HIS. HIS.
2-143-030-08................ (2) 5,001 to 5,199 Before reaching
HIS. 5,250 HIS.
2-143-030-14................ (3) 2,551 to 5,000 Within 250
HIS. additional HIS.
2-143-030R21................ (4) 2,550 or fewer Before reaching
HIS. 2,800 HIS.
2-143-030-22................
2-143-030-23................
------------------------------------------------------------------------
Determination of Drawdown Schedule for Third Stage Turbine Disc and
Shaft Assemblies That Have Operated in Pre and Post SB No. ALF502L 72-
232 Configurations
(h) For ALF502L series turbofan engines, with third stage
turbine disc and shaft assemblies converted from Pre SB No. ALF502L
72-232 configuration to Post SB No. ALF502L 72-232 configuration, do
the following:
(1) Determine the total HIS accumulated on the third stage
turbine disc and shaft assembly at time of installation of third
stage turbine nozzle assembly, P/N 2-141-120-R56/-57.
(2) If the total is 2,800 HIS or more, use the drawdown schedule
in Table 1 of this AD to remove the assembly from service.
(3) If the total is fewer than 2,800 HIS, calculate the
remaining service life using paragraphs 2.A. through 2.B.(4)(i) of
the Accomplishment Instructions of Honeywell SB No. ALF502 72-0004,
Revision 17, dated January 16, 2005.
(i) For ALF502L series turbofan engines, use the drawdown
schedule described in the following Table 2 to remove the assembly
from service:
Table 2.--Drawdown Schedule for Third Stage Turbine Disc and Shaft
Assemblies Operated In Pre and Post SB No. ALF502L 72-232 Configuration
------------------------------------------------------------------------
For third stage turbine disc If HIS on the
and shaft assembly part effective date of Then:
numbers: this AD are:
------------------------------------------------------------------------
(1) 2-143-030-05, 2-143-030- (i) 30,000 or more Remove within 50
08,2-143-030-14. HIS. additional HIS.
(ii) 27,250 to Remove within 250
29,999 HIS. additional HIS.
(iii) Fewer than 27, Remove using Tables
250 HIS. 1 through 5 of
Honeywell SB No.
ALF502 72-0004,
Revision 17, dated
January 16, 2005.
(2) 2-143-030R21, 2-143-030- (i) 24,650 or more Remove within 50
23. HIS. additional HIS.
(ii) 22,150 to Remove within 250
24,649 HIS. additional HIS.
(iii) Fewer than Remove using Tables
22,150 HIS. 1 through 5 of
Honeywell SB No.
ALF502 72-0004,
Revision 17, dated
January 16, 2005.
(3) 2-143-030-22............ (i) 50,000 or more Remove within 50
HIS. additional HIS.
(ii) 49,750 to Remove within 250
49,999 HIS. additional HIS.
(iii) Fewer than Remove using Tables
49,750 HIS. 1 through 5 of
Honeywell SB No.
ALF502 72-0004,
Revision 17, dated
January 16, 2005.
------------------------------------------------------------------------
[[Page 66305]]
ALF502R Series Turbofan Engines
Requirements Brought Forward, and Unchanged From AD 95-04-11
(j) For ALF502R series turbofan engines, remove from service and
replace with a serviceable part third stage turbine disks, P/Ns 2-
143-030-05, 2-143-030-08, and 2-143-030-14, as follows:
(1) For disks that have been installed only with third stage
turbine nozzles P/Ns 2-141-130-52 or 2-141-120-53, remove from
service as follows:
(i) For disks that have accumulated 13,220 or more hours time in
service (TIS) since new on April 13, 1995 (the effective date of AD
95-04-11), within the next 80 hours TIS after December 11, 1990, but
not to exceed the existing cyclic life limit.
(ii) For disks that have accumulated less than 13,220 hours TIS
since new on April 13, 1995, before accumulating more than 13,300
hours TIS since new, but not to exceed the existing cyclic life
limit.
(iii) Thereafter, remove disks before accumulating more than
13,300 hours TIS since new, but not to exceed the existing cyclic
life limit.
(2) For disks that have been installed only with third stage
turbine nozzles, P/Ns 2-141-120-57 or 2-141-120-R56, remove from
service as follows:
(i) For disks that have accumulated 27,420 or more hours TIS
since new on April 13, 1995, within 80 hours TIS after April 13,
1995, but not to exceed the existing cyclic life limit.
(ii) For disks that have accumulated less than 27,420 hours TIS
since new on April 13, 1995, before accumulating more than 27,500
hours TIS since new, but not to exceed the existing cyclic life
limit.
(iii) Thereafter, remove disks before accumulating more than
27,500 hours TIS since new, but not to exceed the existing cyclic
life limit.
(3) For disks that have been installed with both third stage
turbine nozzles, P/Ns 2-141-120-52 or 2-141-120-120-53, and third
stage turbine nozzles P/Ns 2-141-120-57 or 2-141-120-R56, remove
from service as follows:
(i) Determine the prorated hourly life limit using the procedure
defined in the Accomplishment Instructions, Section 2.B.(2) of
Textron Lycoming SB No. ALF502 72-0002, Revision 22, dated December
21, 1992. From this prorated hourly life limit, subtract 80 hours
TIS to determine the compliance threshold.
(ii) For disks that have equaled or exceeded the compliance
threshold on April 13, 1995, within the next 80 hours TIS, but not
to exceed the existing cyclic life limit.
(iii) For disks that have accumulated fewer than the compliance
threshold on April 13, 1995, before accumulating more than the
calculated prorated hourly life limit.
(iv) Thereafter, remove disks at or before accumulating the
prorated hourly life limit, but not to exceed the existing cyclic
life limit.
Alternative Methods of Compliance
(k) The Manager, Los Angeles Aircraft 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.
Special Flight Permits
(l) Under 14 CFR part 39.23, we are limiting the special flight
permits for this AD by allowing a onetime special flight if the disc
life limit has been reached.
Related Information
(m) Honeywell SB No. ALF/LF A72-1085, Revision 1, dated January
16, 2005, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-21802 Filed 11-1-05; 8:45 am]
BILLING CODE 4910-13-P