Airworthiness Directives; Rolls-Royce plc RB211-524 Series Turbofan Engines, 43036-43039 [05-14576]
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Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations
TABLE 4.—BOMBARDIER SERVICE BULLETINS INCORPORATED BY REFERENCE
Bombardier Service Bulletins (including the Component Time Tracking Log Card and Attachments Listed
in Table 5 of this AD)
Revision
level
600–0710 .........................................................................................................................................................
601–0546 .........................................................................................................................................................
604–32–014 .....................................................................................................................................................
01 ............
01 ............
Original ....
Date
December 15, 2003.
December 15, 2003.
May 31, 2002.
TABLE 5.—MESSIER-DOWTY SERVICE BULLETINS INCORPORATED BY REFERENCE
Date
Attached to Bombardier Service Bulletin(s)—
March 19, 2001 ......
March 19, 2001 ......
July 12, 2001 .........
March 19, 2001 ......
March 19, 2001 .....
July 12, 2001 .........
March 19, 2001 ......
March 19, 2001 ......
March 19, 2001 ......
July 12, 2001 .........
600–0710, 601–0546
604–32–014
604–32–014
600–0710, 601–0546
600–0710
600–0710
601–0546
600–0710, 601–0546
600–0710, 601–0546
601–0546
Messier-Dowty Service Bulletin
(attachments)
M–DT
M–DT
M–DT
M–DT
M–DT
M–DT
M–DT
M–DT
M–DT
M–DT
SB104467009/010–32–1 ............................................................................................................
SB19090–32–4 ...........................................................................................................................
SB20020–32–5 ...........................................................................................................................
SB200814001–32–3 ...................................................................................................................
SB200922001/2–32–6 ................................................................................................................
SB200924003/004–32–16 ..........................................................................................................
SB6100–32–10 ...........................................................................................................................
SB6500–32–1 .............................................................................................................................
SB7200–32–6 .............................................................................................................................
SB7300–32–16 ...........................................................................................................................
TABLE 6.—CANADAIR TEMPORARY REVISIONS INCORPORATED BY REFERENCE
Canadair temporary revision
5–116
5–190
5–191
5–192
5–2–6
5–204
5–205
5–206
................................................................................................................................
................................................................................................................................
................................................................................................................................
................................................................................................................................
................................................................................................................................
................................................................................................................................
................................................................................................................................
................................................................................................................................
Issued in Renton, Washington, on July 11,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–14175 Filed 7–25–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002–NE–40–AD; Amendment
39–14202; AD 2005–15–13]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211–524 Series Turbofan
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate jul<14>2003
23:50 Jul 25, 2005
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April
April
April
April
April
April
April
April
11,
11,
11,
11,
11,
11,
11,
11,
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Rolls
Royce plc (RR) RB211–524 series
turbofan engines with certain part
number (P/N) intermediate pressure (IP)
compressor stage 5 disks installed. This
AD requires new reduced IP compressor
stage 5 disk cyclic limits. This AD also
requires removing from service affected
disks that already exceed the new
reduced cyclic limit, and removing
other affected disks before exceeding
their cyclic limits, using a drawdown
schedule. This AD results from the
discovery of cracks in the cooling air
hole areas of the disk front spacer arm.
We are issuing this AD to prevent IP
compressor stage 5 disk failure, which
could result in uncontained engine
failure and possible damage to the
airplane.
This AD becomes effective
August 30, 2005. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of August 30, 2005.
DATES:
PO 00000
Frm 00020
Applicable Canadair
time-limits/maintenance check manual
Date
Fmt 4700
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2002
2002
2002
2002
2002
2002
2002
2002
........
........
........
........
........
........
........
........
Manual
section
PSP 605 ................
PSP 601–5 ............
PSP 601–5 ............
PSP 601–5 ............
CL–604 ..................
PSP 601A–5 ..........
PSP 601A–5 ..........
PSP 601A–5 ..........
5–10–10
5–10–10
5–10–11
5–10–12
5–10–10
5–10–10
5–10–11
5–10–12
You can get the service
information identified in this AD from
Rolls-Royce plc, P.O. Box 31 Derby,
DE248BJ, United Kingdom; telephone
011–44–1332–242424; fax 011–44–
1332–249936.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA. You
may examine the service information, at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at
the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
ADDRESSES:
Ian
Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
FOR FURTHER INFORMATION CONTACT:
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Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations
5299; telephone (781) 238–7178; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to (RR) RB211–524 series
turbofan engines with certain P/N IP
compressor stage 5 disks installed. We
published the proposed AD in the
Federal Register on February 2, 2005
(70 FR 5390). That action proposed to
require:
• Establishing new reduced IP
compressor stage 5 disk cyclic limits.
• Removing from service affected
disks that already exceed the new
reduced cyclic limit.
• Removing other affected disks
before exceeding their cyclic limits,
using a drawdown schedule.
• Allowing optional inspections at
each shop visit or an on-wing eddy
current inspection to extend the disk
life beyond the specified life.
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8:00 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays.
See ADDRESSES for the location.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
There are about 939 RR RB211–524
series turbofan engines of the affected
design in the worldwide fleet. We
estimate that this AD will affect about
35 engines installed on airplanes of U.S.
registry. We also estimate that it will
take about 8 work hours per engine to
perform an inspection, and 300 work
hours per engine to replace an IP
compressor stage 5 disk. The average
labor rate is $65 per work hour.
Required parts will cost about $49,000
per engine. Based on these figures, we
estimate the total cost of the AD to U.S.
operators to be $2,415,700.
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the National Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 2002–NE–40–
AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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:
I
2005–15–13 Rolls-Royce plc: Amendment
39–14202. Docket No. 2002–NE–40–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 30, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Rolls-Royce plc
(RR) RB211–524 series turbofan engines
listed in the following Table 1, with
intermediate pressure (IP) compressor stage 5
disk part numbers (P/Ns) listed in Table 2 of
this AD, installed.
TABLE 1.—ENGINE MODELS AFFECTED
¥524B–02
¥524B2–19
¥524D4–B–19
¥524G2–19
¥524H2–T–19
¥524B–B–02
¥524B2–B–19
¥524D4X–19
¥524G2–T–19
¥524H–36
¥524B3–02
¥524C2–19
¥524D4X–B–19
¥524G3–19
¥524H–T–36
¥524B4–02
¥524C2–B–19
¥524D4–39
¥524G3–T–19
¥524B4–D–02
¥524D4–19
¥524D4–B–39
¥524H2–19
These engines are installed on, but not
limited to, Boeing 747, 767, and Lockheed L–
1011 airplanes.
TABLE 2.—IP COMPRESSOR STAGE 5 DISK P/NS AFFECTED
LK60130
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Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations
TABLE 2.—IP COMPRESSOR STAGE 5 DISK P/NS AFFECTED—Continued
LK83283
UL19132
UL36821
UL36981
UL37080
UL12290
UL20785
UL36977
UL36982
UL37081
UL15743
UL20832
UL36978
UL36983
UL37082
Unsafe Condition
(d) This AD results from discovery of
cracks in the cooling air hole areas of the disk
front spacer arm. The actions specified in
this AD are intended to prevent IP
compressor stage 5 disk failure, which could
UL15744
UL23291
UL36979
UL37078
UL37083
result in uncontained engine failure 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.
UL15745
UL25011
UL36980
UL37079
UL37084
Cycle Limits
(f) Change the service cyclic limits
contained in the Time Limits Manual, 05–
10–01, for the IP compressor stage 5 discs
installed in the engine models listed in the
following Table 3, within 30 days after the
effective date of this AD.
TABLE 3.—CYCLIC LIFE LIMITS WITHOUT QUALIFYING MAGNETIC PARTICLE INSPECTION (MPI) OR EDDY CURRENT
INSPECTION (ECI)
Engine models
Date of reduced life limit
–524G2, G2–T, G3, G3–T, H2, H2–T, H–36,
H–T–36
–524D4, D4–
B, D4–B–39,
D4X, D4X–B,
D4–39
CIS
November 30, 2002 ........................................
April 1, 2003 ....................................................
December 1, 2003 ..........................................
December 1, 2004 ..........................................
December 1, 2005 ..........................................
December 1, 2008 ..........................................
13,500 cycles-in-service (CIS) .......................
13,500 CIS .....................................................
12,000 CIS .....................................................
11,000 CIS .....................................................
11,000 CIS .....................................................
7,830 CIS .......................................................
16,150
13,500
13,500
13,500
12,000
8,700
Optional Inspections
(g) Before December 1, 2008, optional
inspections are allowed at each shop visit or
on-wing to extend the disk life. Guidance for
these inspections is provided in paragraphs
(h) or (i) of this AD.
Optional Inspections at Shop Visit
(h) Perform optional inspections at shop
visit, as follows:
(1) Remove corrosion protection from IP
stage 5 disk. Information on corrosion
protection removal can be found in the
Engine Manual.
(2) Visual-inspect and binocular-inspect
the IP stage 5 disk for corrosion pitting at the
cooling air holes and defender holes in the
disk front spacer arm. Follow paragraph 3.C.
of the Accomplishment Instructions of RR
MSB No. RB.211–72–D428, Revision 3, dated
June 30, 2003. Information on disk corrosion
pitting limits can be found in the Engine
Manual.
(i) If the disk has corrosion pitting in
excess of limits, remove the disk from
service.
(ii) If the disk is free from corrosion pitting,
MPI the entire disk. Information on MPI can
be found in the Engine Manual. If the disk
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23:50 Jul 25, 2005
Jkt 205001
passes MPI and no cracks are found,
complete all other inspections, re-apply
corrosion protection to disk, and return the
disk to service in accordance with the cyclic
limits allowed by paragraph (k) of this AD.
Information on MPI limits can be found in
the Engine Manual. Information on reapplying corrosion protection can be found
in RR Repair FRS5900.
(iii) If the disk has corrosion pitting within
limits, ECI all disk cooling air holes, defender
holes, and inner and outer faces. Follow
paragraph 3.D. of the Accomplishment
Instructions of RR MSB No. RB.211–72–
D428, Revision 3, dated June 30, 2003.
Information on corrosion pitting limits can be
found in the Engine Manual. If the disk
passes ECI and no cracks are found, MPI the
entire disk. Information on MPI can be found
in the Engine Manual. If the disk passes MPI
and no cracks are found, re-apply corrosion
protection to disk, and return the disk to
service in accordance with the cyclic limits
allowed by paragraph (k) of this AD.
Optional On-Wing EC Inspections
(i) For RB211–524B2/C2 and RB211–
524B4/D4 engine models, an on-wing ECI of
the IP compressor stage 5 disk may be
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
–524B2, B2–
B, C2, C2–B
CIS
16,000
13,500
13,500
12,000
12,000
8,900
–524B–02, B–
B–02, B3–02,
B4–02, B4–D–
02
CIS
16,200
14,000
14,000
12,000
12,000
9,000
performed only once between shop visit
inspections. Follow paragraphs 3.A. through
3.F. of the Accomplishment Instructions of
RR SB No. RB.211–72–E148, dated March 13,
2003, and RR SB No. RB.211–72–E150,
Revision 1, dated June 4, 2003, respectively,
to do the ECI. If the disk passes the ECI and
no cracks are found, an extension is allowed
as specified in paragraph (k) of this AD.
Definition of Shop Visit
(j) For the purposes of this AD, a shop visit
is defined as the separation of an engine
major case flange. This definition excludes
shop visits when only field maintenance type
activities are performed in lieu of performing
them on-wing. (i.e., for purposes such as to
perform an on-wing inspection of a tail
engine installation on a Lockheed L–1011
airplane).
Cyclic Life Extension
(k) Disks that pass an optional inspection
may remain in service after that inspection
for the additional cycles listed in the
following Table 4, until the next inspection,
or December 1, 2008, or until the cyclic life
limit published in the Time Limits Manual
is reached, whichever occurs first.
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Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations
TABLE 4.—CYCLIC LIFE EXTENSION
–524G2, G2–
T, G3, G3–T,
H2, H2–T, H–
36, H–T–36
(cycles)
1,600
3,800
1,000
Engine models
–524D4, D4–
B, D4–B–39,
D4X, D4X–B,
D4–39
(cycles)
2,000
4,500
1,200
Extension After Passing MPI
Extension After Passin In-Shop ECI
Extension After Passing On-Wing ECI
Disks That Have Been Intermixed Between
Engine Models
(l) Information on intermixing disks
between engine models can be found in the
RR Time Limits Manual, 05–00–01.
Reporting Requirement
(o) Report findings of all inspections of the
IP stage 5 disk using paragraph 3.B.(2) of the
Accomplishment Instructions of RR ASB
RB.211–72-D428, Revision 3, dated June 30,
2003. The Office of Management and Budget
(OMB) has approved the reporting
requirements specified in Paragraph 3.B. of
the Accomplishment Instructions of RR ASB
RB.211–72-D428, Revision 3, dated June 30,
2003, and assigned OMB control number
2120–0056.
Alternative Methods of Compliance
(m) 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.
Credit for Previous Inspections
(n) Inspections done using RR SB No.
RB.211–72-E150, dated April 17, 2003 are
acceptable in meeting the requirements of
this AD.
Material Incorporated by Reference
(p) You must use Rolls-Royce plc Service
Bulletins listed in Table 5 of this AD to
perform the actions required by this AD. The
–524B–02, B–
B–02, B3–02,
B4–02, B4–D–
02
(cycles)
–524B2, B2–
B, C2, C2–B
(cycles)
2,000
4,500
1,200
2,000
4,500
1,200
Director of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. You can get a copy from
Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ,
United Kingdom; telephone 011–44–1332–
242424; fax 011–44–1332–249936. You can
review copies by appointment, at the FAA,
New England Region, Office of the Regional
Counsel, 12 New England Executive Park,
Burlington, MA; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 5.—INCORPORATION BY REFERENCE
Service bulletin
Page number
shown on the page
Revision
Date shown on
the page
RB.211–72–D428, including Appendices 1 through 4, dated June 30, 2003 .......
RB.211–72–E148 Total Pages—83 .......................................................................
RB.211–72–E150 Total Pages—72 .......................................................................
All ...........................
All ...........................
All ...........................
3 .............................
Original ..................
1 .............................
June 30, 2003.
March 13, 2003.
June 4, 2003.
Related Information
(q) CAA airworthiness directive 006–04–
2002, dated April 2002, also addresses the
subject of this AD.
Issued in Burlington, Massachusetts, on
July 18, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–14576 Filed 7–25–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30451; Amdt. No. 3127]
Standard Instrument Approach
Procedures, Weather Takeoff
Minimums; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
AGENCY:
ACTION:
Final rule.
VerDate jul<14>2003
23:50 Jul 25, 2005
Jkt 205001
SUMMARY: This amendment establishes,
amends, suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) and/or Weather Takeoff
Minimums for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
This rule is effective July 26,
2005. The compliance date for each
SIAP and/or Weather Takeoff
Minimums is specified in the
amendatory provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of July 26,
2005.
DATES:
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
Availability of matters
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591;
2. The FAA Regional Office of the
region in which the affected airport is
located;
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. The National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
For Purchase—Individual SIAP and
Weather Takeoff Minimums copies may
be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
ADDRESSES:
E:\FR\FM\26JYR1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 142 (Tuesday, July 26, 2005)]
[Rules and Regulations]
[Pages 43036-43039]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-14576]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-40-AD; Amendment 39-14202; AD 2005-15-13]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211-524 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls Royce plc (RR) RB211-524 series turbofan engines with certain
part number (P/N) intermediate pressure (IP) compressor stage 5 disks
installed. This AD requires new reduced IP compressor stage 5 disk
cyclic limits. This AD also requires removing from service affected
disks that already exceed the new reduced cyclic limit, and removing
other affected disks before exceeding their cyclic limits, using a
drawdown schedule. This AD results from the discovery of cracks in the
cooling air hole areas of the disk front spacer arm. We are issuing
this AD to prevent IP compressor stage 5 disk failure, which could
result in uncontained engine failure and possible damage to the
airplane.
DATES: This AD becomes effective August 30, 2005. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of August 30, 2005.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ, United Kingdom;
telephone 011-44-1332-242424; fax 011-44-1332-249936.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information, at the FAA,
New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_locations.html.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-
[[Page 43037]]
5299; telephone (781) 238-7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to (RR) RB211-524 series
turbofan engines with certain P/N IP compressor stage 5 disks
installed. We published the proposed AD in the Federal Register on
February 2, 2005 (70 FR 5390). That action proposed to require:
Establishing new reduced IP compressor stage 5 disk cyclic
limits.
Removing from service affected disks that already exceed
the new reduced cyclic limit.
Removing other affected disks before exceeding their
cyclic limits, using a drawdown schedule.
Allowing optional inspections at each shop visit or an on-
wing eddy current inspection to extend the disk life beyond the
specified life.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8:00 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
There are about 939 RR RB211-524 series turbofan engines of the
affected design in the worldwide fleet. We estimate that this AD will
affect about 35 engines installed on airplanes of U.S. registry. We
also estimate that it will take about 8 work hours per engine to
perform an inspection, and 300 work hours per engine to replace an IP
compressor stage 5 disk. The average labor rate is $65 per work hour.
Required parts will cost about $49,000 per engine. Based on these
figures, we estimate the total cost of the AD to U.S. operators to be
$2,415,700.
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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the National Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2002-NE-40-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2005-15-13 Rolls-Royce plc: Amendment 39-14202. Docket No. 2002-NE-
40-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
30, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Rolls-Royce plc (RR) RB211-524 series
turbofan engines listed in the following Table 1, with intermediate
pressure (IP) compressor stage 5 disk part numbers (P/Ns) listed in
Table 2 of this AD, installed.
Table 1.--Engine Models Affected
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
-524B-02 -524B-B-02 -524B3-02 -524B4-02 -524B4-D-02
-524B2-19 -524B2-B-19 -524C2-19 -524C2-B-19 -524D4-19
-524D4-B-19 -524D4X-19 -524D4X-B-19 -524D4-39 -524D4-B-39
-524G2-19 -524G2-T-19 -524G3-19 -524G3-T-19 -524H2-19
-524H2-T-19 -524H-36 -524H-T-36
----------------------------------------------------------------------------------------------------------------
These engines are installed on, but not limited to, Boeing 747,
767, and Lockheed L-1011 airplanes.
Table 2.--IP Compressor Stage 5 Disk P/Ns Affected
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
LK60130 LK65932 LK69021 LK81269 LK83282
[[Page 43038]]
LK83283 UL12290 UL15743 UL15744 UL15745
UL19132 UL20785 UL20832 UL23291 UL25011
UL36821 UL36977 UL36978 UL36979 UL36980
UL36981 UL36982 UL36983 UL37078 UL37079
UL37080 UL37081 UL37082 UL37083 UL37084
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from discovery of cracks in the cooling air
hole areas of the disk front spacer arm. The actions specified in
this AD are intended to prevent IP compressor stage 5 disk failure,
which could result in uncontained engine failure 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.
Cycle Limits
(f) Change the service cyclic limits contained in the Time
Limits Manual, 05-10-01, for the IP compressor stage 5 discs
installed in the engine models listed in the following Table 3,
within 30 days after the effective date of this AD.
Table 3.--Cyclic Life Limits Without Qualifying Magnetic Particle Inspection (MPI) or Eddy Current Inspection
(ECI)
----------------------------------------------------------------------------------------------------------------
Engine models
-------------------------------------------------------------------------
-524D4, D4-B, -524B-02, B-B-
Date of reduced life limit -524G2, G2-T, G3, G3-T, D4-B-39, D4X, -524B2, B2-B, 02, B3-02, B4-
H2, H2-T, H-36, H-T-36 D4X-B, D4-39 C2, C2-B CIS 02, B4-D-02
CIS CIS
----------------------------------------------------------------------------------------------------------------
November 30, 2002..................... 13,500 cycles-in-service 16,150 16,000 16,200
(CIS).
April 1, 2003......................... 13,500 CIS.............. 13,500 13,500 14,000
December 1, 2003...................... 12,000 CIS.............. 13,500 13,500 14,000
December 1, 2004...................... 11,000 CIS.............. 13,500 12,000 12,000
December 1, 2005...................... 11,000 CIS.............. 12,000 12,000 12,000
December 1, 2008...................... 7,830 CIS............... 8,700 8,900 9,000
----------------------------------------------------------------------------------------------------------------
Optional Inspections
(g) Before December 1, 2008, optional inspections are allowed at
each shop visit or on-wing to extend the disk life. Guidance for
these inspections is provided in paragraphs (h) or (i) of this AD.
Optional Inspections at Shop Visit
(h) Perform optional inspections at shop visit, as follows:
(1) Remove corrosion protection from IP stage 5 disk.
Information on corrosion protection removal can be found in the
Engine Manual.
(2) Visual-inspect and binocular-inspect the IP stage 5 disk for
corrosion pitting at the cooling air holes and defender holes in the
disk front spacer arm. Follow paragraph 3.C. of the Accomplishment
Instructions of RR MSB No. RB.211-72-D428, Revision 3, dated June
30, 2003. Information on disk corrosion pitting limits can be found
in the Engine Manual.
(i) If the disk has corrosion pitting in excess of limits,
remove the disk from service.
(ii) If the disk is free from corrosion pitting, MPI the entire
disk. Information on MPI can be found in the Engine Manual. If the
disk passes MPI and no cracks are found, complete all other
inspections, re-apply corrosion protection to disk, and return the
disk to service in accordance with the cyclic limits allowed by
paragraph (k) of this AD. Information on MPI limits can be found in
the Engine Manual. Information on re-applying corrosion protection
can be found in RR Repair FRS5900.
(iii) If the disk has corrosion pitting within limits, ECI all
disk cooling air holes, defender holes, and inner and outer faces.
Follow paragraph 3.D. of the Accomplishment Instructions of RR MSB
No. RB.211-72-D428, Revision 3, dated June 30, 2003. Information on
corrosion pitting limits can be found in the Engine Manual. If the
disk passes ECI and no cracks are found, MPI the entire disk.
Information on MPI can be found in the Engine Manual. If the disk
passes MPI and no cracks are found, re-apply corrosion protection to
disk, and return the disk to service in accordance with the cyclic
limits allowed by paragraph (k) of this AD.
Optional On-Wing EC Inspections
(i) For RB211-524B2/C2 and RB211-524B4/D4 engine models, an on-
wing ECI of the IP compressor stage 5 disk may be performed only
once between shop visit inspections. Follow paragraphs 3.A. through
3.F. of the Accomplishment Instructions of RR SB No. RB.211-72-E148,
dated March 13, 2003, and RR SB No. RB.211-72-E150, Revision 1,
dated June 4, 2003, respectively, to do the ECI. If the disk passes
the ECI and no cracks are found, an extension is allowed as
specified in paragraph (k) of this AD.
Definition of Shop Visit
(j) For the purposes of this AD, a shop visit is defined as the
separation of an engine major case flange. This definition excludes
shop visits when only field maintenance type activities are
performed in lieu of performing them on-wing. (i.e., for purposes
such as to perform an on-wing inspection of a tail engine
installation on a Lockheed L-1011 airplane).
Cyclic Life Extension
(k) Disks that pass an optional inspection may remain in service
after that inspection for the additional cycles listed in the
following Table 4, until the next inspection, or December 1, 2008,
or until the cyclic life limit published in the Time Limits Manual
is reached, whichever occurs first.
[[Page 43039]]
Table 4.--Cyclic Life Extension
----------------------------------------------------------------------------------------------------------------
-524G2, G2-T,
G3, G3-T, H2, -524D4, D4-B, -524B2, B2-B, -524B-02, B-B-
Engine models H2-T, H-36, H- D4-B-39, D4X, C2, C2-B 02, B3-02, B4-
T-36 (cycles) D4X-B, D4-39 (cycles) 02, B4-D-02
(cycles) (cycles)
----------------------------------------------------------------------------------------------------------------
Extension After Passing MPI 1,600 2,000 2,000 2,000
Extension After Passin In-Shop ECI 3,800 4,500 4,500 4,500
Extension After Passing On-Wing ECI 1,000 1,200 1,200 1,200
----------------------------------------------------------------------------------------------------------------
Disks That Have Been Intermixed Between Engine Models
(l) Information on intermixing disks between engine models can
be found in the RR Time Limits Manual, 05-00-01.
Alternative Methods of Compliance
(m) 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.
Credit for Previous Inspections
(n) Inspections done using RR SB No. RB.211-72-E150, dated April
17, 2003 are acceptable in meeting the requirements of this AD.
Reporting Requirement
(o) Report findings of all inspections of the IP stage 5 disk
using paragraph 3.B.(2) of the Accomplishment Instructions of RR ASB
RB.211-72-D428, Revision 3, dated June 30, 2003. The Office of
Management and Budget (OMB) has approved the reporting requirements
specified in Paragraph 3.B. of the Accomplishment Instructions of RR
ASB RB.211-72-D428, Revision 3, dated June 30, 2003, and assigned
OMB control number 2120-0056.
Material Incorporated by Reference
(p) You must use Rolls-Royce plc Service Bulletins listed in
Table 5 of this AD to perform the actions required by this AD. The
Director of the Federal Register approved the incorporation by
reference of this service bulletin in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. You can get a copy from Rolls-Royce plc,
P.O. Box 31 Derby, DE248BJ, United Kingdom; telephone 011-44-1332-
242424; fax 011-44-1332-249936. You can review copies by
appointment, at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
Table 5.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Page number shown on the
Service bulletin page Revision Date shown on the page
----------------------------------------------------------------------------------------------------------------
RB.211-72-D428, including All....................... 3......................... June 30, 2003.
Appendices 1 through 4, dated
June 30, 2003.
RB.211-72-E148 Total Pages--83. All....................... Original.................. March 13, 2003.
RB.211-72-E150 Total Pages--72. All....................... 1......................... June 4, 2003.
----------------------------------------------------------------------------------------------------------------
Related Information
(q) CAA airworthiness directive 006-04-2002, dated April 2002,
also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on July 18, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-14576 Filed 7-25-05; 8:45 am]
BILLING CODE 4910-13-P
