Airworthiness Directives; Honeywell International Inc., (Formerly AlliedSignal, Inc. and Textron Lycoming) ALF502L Series and ALF502R Series Turbofan Engines, 66302-66305 [05-21802]
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66302
Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
Engine model
7R4D/D1/E/E1 ...............
Inspect per
manual
section
Engine manual part
number (P/N)
Part nomenclature
785058 and 785059 .....
All HPT Stage 1—2 Disks and Hubs .................
All LPT Stage 3—6 Disks and Hubs ..................
All HPT Stage 1 Disk Web Cooling Holes .........
72–51–00
72–52–00
72–51–06
Inspection/check
Inspection/Check-03.
Inspection/Check-03.
Inspection/Check-02.
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.
(2) For the purposes of these mandatory
inspections, piece-part opportunity means:
(i) The part is considered completely
disassembled when done in accordance with
the disassembly instructions in the
manufacturer’s engine manual; and
(ii) The part has accumulated more than
100 cycles-in-service since the last piece-part
opportunity inspection, provided that the
part was not damaged or related to the cause
for its removal from the engine.’’
Issued in Burlington, Massachusetts, on
October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–21804 Filed 11–1–05; 8:45 am]
Alternative Methods of Compliance
Federal Aviation Administration
(g) You must perform these mandatory
inspections using the ALS of the Instructions
for Continued Airworthiness and the
applicable Engine Manual unless you receive
approval to use an alternative method of
compliance under paragraph (h) of this AD.
Section 43.16 of the Federal Aviation
Regulations (14 CFR 43.16) may not be used
to approve alternative methods of
compliance or adjustments to the times in
which these inspections must be performed.
(h) 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.
Maintaining Records of the Mandatory
Inspections
(i) You have met the requirements of this
AD when you change the manufacturer’s
Instructions for Continued Airworthiness
ALS specified in paragraph (f) of this AD,
and, for air carriers operating under part 121
of the Federal Aviation Regulations (14 CFR
part 121), when you modify your continuous
airworthiness maintenance plan to reflect
those changes. You do not need to record
each piece-part inspection as compliance to
this AD but you must maintain records of
those inspections according to the
regulations governing your operation. For air
carriers operating under part 121, you may
use either the system established to comply
with section 121.369 or an alternative
accepted by your principal maintenance
inspector if that alternative:
(1) Includes a method for preserving and
retrieving the records of the inspections
resulting from this AD; and
(2) Meets the requirements of section
121.369(c); and
(3) Maintains the records either
indefinitely or until the work is repeated.
(j) These record keeping requirements
apply only to the records used to document
the mandatory inspections required as a
result of revising the ALS of the Instructions
for Continued Airworthiness as specified in
paragraph (f) of this AD, and do not alter or
amend the record keeping requirements for
any other AD or regulatory requirement.
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
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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-aneadcomment@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 datestamp 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
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Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
FAA’s Determination and Requirements
of the Proposed AD
the closing date and may amend the
proposed AD in light of those
comments.
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.
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.
Actions Since AD 95–04–11 Was Issued
Costs of Compliance
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.
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.
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
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.
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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
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66303
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.
§ 39.13
[Amended]
2. The FAA amends § 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.
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Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
January 3, 2006.
Unsafe Condition
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.
(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
For third stage turbine disc and shaft assembly
P/Ns
If hours-in-service (HIS) on the effective date
of this AD are
2–143–030–05 ....................................................
2–143–030–08 ....................................................
2–143–030–14 ....................................................
2–143–030R21 ...................................................
2–143–030–22.
2–143–030–23.
(1)
(2)
(3)
(4)
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
5,200
5,001
2,551
2,550
or more HIS ......................................
to 5,199 HIS .....................................
to 5,000 HIS .....................................
or fewer HIS .....................................
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.
Then remove
Within 50 additional HIS.
Before reaching 5,250 HIS.
Within 250 additional HIS.
Before reaching 2,800 HIS.
(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 and shaft assembly
part numbers:
If HIS on the effective date of this AD are:
(1) 2–143–030–05, 2–143–030–08,2–143–030–
14.
(i) 30,000 or more HIS .....................................
Remove within 50 additional HIS.
(ii) 27,250 to 29,999 HIS .................................
(iii) Fewer than 27, 250 HIS ............................
Remove within 250 additional HIS.
Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17,
dated January 16, 2005.
Remove within 50 additional HIS.
Remove within 250 additional HIS.
Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17,
dated January 16, 2005.
Remove within 50 additional HIS.
Remove within 250 additional HIS.
Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17,
dated January 16, 2005.
(2) 2–143–030R21, 2–143–030–23 ...................
(i) 24,650 or more HIS .....................................
(ii) 22,150 to 24,649 HIS .................................
(iii) Fewer than 22,150 HIS ..............................
(3) 2–143–030–22 ..............................................
(i) 50,000 or more HIS .....................................
(ii) 49,750 to 49,999 HIS .................................
(iii) Fewer than 49,750 HIS ..............................
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Then:
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Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
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
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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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
User Input to the Aviation Weather
Technology Transfer (AWTT) Board
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Proposed rule; notice of public
meeting.
AGENCY:
SUMMARY: The FAA will hold an
informal public meeting to seek aviation
weather user input on convective
weather products. Details: November 10,
2005; Orlando Orange County
Convention Center, 9800 International
Drive, Room N210A, Orlando, Florida
32819, 1 p.m. to 5 p.m. The objective of
this meeting is to provide an
opportunity for interested Government
and commercial sector representatives
who use Government-provided aviation
weather information in operational
decision-making to provide input on
FAA’s plans for implementing new
convective weather products.
DATES: The meeting will be held at the
Orlando Orange County Convention
Center, 9800 International Drive, Room
N210A, Orlando, Florida 32819; Times:
1 p.m. to 5 p.m. on November 10, 2005.
FOR FURTHER INFORMATION CONTACT: Debi
Bacon, Air Traffic Administration, 800
Independence Ave., SW., Washington,
DC 20591; telephone number (202) 385–
7705; Fax: (202) 385–7701; e-mail:
debi.bacon@faa.gov.
SUPPLEMENTARY INFORMATION:
History
In 1999, the FAA established an
Aviation Weather Technology Transfer
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66305
(AWTT) Board to manage the orderly
transfer of weather capabilities and
products from research and
development (R&D) into operations. The
Director of the National Airspace (NAS)
Weather Office, Operations Planning,
Air Traffic Organization chairs the
AWTT Board. The board is composed of
stakeholders in the Air Traffic and
Aviation Safety organizations in the
Federal Aviation Administration and
the Office of Climate, Water and
Weather Services, the Office of Science
and Technology, and the National
Center for Environmental Predictions
(NCEP) in the National Weather Service.
The AWTT Board meets semiannually or as needed to determine the
readiness of weather R&D products for
experimental use or full operational use
for meteorologists or for end users. The
board makes the determination based on
technical and operational readiness,
cost and benefits, user needs and budget
considerations.
FAA has the sole responsibility and
authority to make decisions intended to
provide a safe, secure, and efficient U.S.
national airspace system. However, it
behooves FAA to not make decisions in
a vacuum. Rather, FAA is seeking
inputs from the user community before
decisions are finalized.
Industry users are invited to
participate in one-day meetings about
three times per year to give specific
feedback to the Government. Meetings
will be focused on a specific domain
(e.g. terminal, enroute) or specific
weather phenomena (e.g. turbulence,
convection). Meetings will include a
time for users to provide input on
specific weather products and aviation
weather road maps and to surface issues
or concerns with those products. The
industry review sessions will be
announced in the Federal Register and
open to all interested parties.
This meeting is the industry session
focused on convective weather
products, roadmaps and research
activities.
Meeting Procedures
(a) The meeting will be informal in
nature and will be conducted by
representatives of the FAA
Headquarters.
(b) The meeting will be open to all
persons on a space-available basis.
Every effort was made to provide a
meeting site with sufficient seating
capacity for the expected participation.
There will be neither admission fee nor
other charge to attend and participate.
This meeting is being held in
conjunction with the NBAA Convention
2005. There is a charge to attend the
NBAA convention; however, any person
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]]>Agencies
[Federal Register Volume 70, Number 211 (Wednesday, November 2, 2005)]
[Proposed Rules]
[Pages 66302-66305]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21802]
-----------------------------------------------------------------------
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
