[Federal Register: January 20, 2004 (Volume 69, Number 12)]
[Rules and Regulations]
[Page 2661-2663]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20ja04-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-12-AD; Amendment 39-13434; AD 2004-01-20]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -
524G2, -524G3, and -524H series, and RB211-535C and -535E series
turbofan engines with high pressure compressor (HPC) stage 3 disc
assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036,
UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD
allows disc assemblies not modified by a certain RR service bulletin to
reach their full life only after the disc assemblies are modified with
anti-corrosion protection. This AD results from the manufacturer's
reassessment of the corrosion risk on HPC stage 3 disc assemblies that
have not yet been modified with sufficient application of anti-
corrosion protection. We are issuing this AD to prevent corrosion-
induced uncontained disc failure, resulting in damage to the airplane.
DATES: This AD becomes effective February 24, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 24, 2004.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone:
011-44-1332-242424; fax: 011-44-1332-245-418.
You may examine the AD docket, by appointment, 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
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine And Propeller Directorate, 12 New
England Executive Park; Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to RR RB211-22B series, RB211-524B, -524C2, -524D4, -524G2, -524G3, and
-524H series, and RB211-535C and -535E series turbofan engines with HPC
stage 3 disc assemblies, P/Ns LK46210, LK58278, LK67634, LK76036,
UL11706, UL15358, UL22577, UL22578, and UL24738 installed. We published
the proposed AD in the Federal Register on July 30, 2003 (68 FR 44672).
That action proposed to allow disc assemblies not modified by a certain
RR service bulletin to reach their full life only after the disc
assemblies are modified with anti-corrosion protection.
[[Page 2662]]
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Add a Service Bulletin Reference
Three commenters request that the FAA include a reference to RR
Mandatory Service Bulletin (MSB) No. RB.211-72-9661, since the AD
action is based on compliance with the procedures in this service
bulletin.
We agree that the AD action is based on performing the procedures
in (MSB) No. RB.211-72-9661, however, we included all pertinent
compliance requirements in the AD and chose to not incorporate by
reference that MSB. However, because that MSB is the basis for the AD
action, we have added a reference to it in the Related Information
paragraph.
Request To Change Compliance Date
One commenter requests that the AD be changed to have the same
compliance dates as Service Bulletin (SB) No. RB.211-72-9434, Revision
4, dated January 12, 2002. The commenter points out that the SB
compliance time for discs in service more than 12 years is from the
date of introduction of the original SB. The commenter also points out
that the compliance time is based on the date of the SB revision date
of January 4, 2002, and would, therefore, require rework to be
completed before January 4, 2007.
We partially agree. While the commenter is correct regarding the
compliance date differences between the AD and the SB, the intent of
the SB is met because the AD is consistent with the SB by mandating
rework before exceeding the upper cyclic limit of the discs. Further,
we agree that removal of discs in service more than 12 years from the
date of the SB revision date, would require the AD to reference 1990
instead of 1992. Therefore, we have changed this date in the AD
accordingly.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Changes to 14 CFR Part 39--Effect on the AD
On July 10, 2002, the FAA published a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. That
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. The
material previously was included in each individual AD. Since the
material is included in 14 CFR part 39, we will not include it in
future AD actions.
Cost of Compliance
There are about 2,000 RR RB211-22B series, RB211-524B, -524C2, -
524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E
series turbofan engines of the affected design in the worldwide fleet.
We estimate that 1,000 engines installed on airplanes of U.S. registry
would be affected by this AD. We also estimate that it would take about
31 work hours per engine to perform the actions, and that the average
labor rate is $65 per work hour. Required parts would cost about
$38,000 per engine. Based on these figures, the total cost of the AD to
U.S. operators is estimated to be $40,015,000.
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. 2003-NE-12-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 (AD):
2004-01-20 Rolls-Royce plc: Amendment 39-13434. Docket No. 2003-NE-
12-AD.
Effective Date
(a) This AD becomes effective February 24, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211-22B series,
RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and
RB211-535C and--535E series turbofan engines with high pressure
compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns)
LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577,
UL22578, and UL24738 installed. These engines are installed on, but
not limited to, Boeing 747, Boeing 757, Boeing 767, Lockheed L-1011,
and Tupolev Tu204 series airplanes.
Unsafe Condition
(d) This AD results from the manufacturer's reassessment of the
corrosion risk on HPC stage 3 disc assemblies that have not yet been
modified with sufficient application of anti-corrosion protection.
The actions specified in this AD are intended to prevent corrosion-
induced uncontained disc failure, resulting in damage to the
airplane.
Compliance
(e) Compliance with this AD is required as indicated, unless
already done.
Removal of HPC Stage 3 Discs
(f) Remove from service affected HPC stage 3 disc assemblies
identified in the following Table 1, using one of the following
criteria:
[[Page 2663]]
Table 1.--Affected HPC Stage 3 Disc Assemblies
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Rework band for
Rework band for cyclic life
cyclic life Rework band for accumulated on P/
accumulated on cyclic life Ns LK76036,
disc assemblies P/ accumulated on UL11706, UL15358,
Engine model Ns LK46210 and disc assembly P/N UL22577, UL22578,
LK58278 (pre RR LK67634 (pre RR SB and UL24738 disc
service bulletin No.RB.211-72-5420) assemblies (pre
(SB) No. RB.211- RR SB No. RB.211-
72-5420) 72-9434)
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-22B series........................................... 4,000-6,200 7,000-10,000 11,500-14,000
-535E4 series......................................... N/A N/A 9,000-15,000
-524B-02, B-B-02, B3-02, and B4 series, Pre and SB No. 4,000-6,000 7,000-9,000 11,500-14,000
72-7730..............................................
-524B2 and C2 series, Pre SB No. 72-7730.............. 4,000-6,000 7,000-9,000 11,500-14,000
-524B2-B-19 and C2-B-19, SB No. 72-7730............... 4,000-6,000 7,000-9,000 8,500-11,000
-524D4 series, Pre SB No. 72-7730..................... 4,000-6,000 7,000-9,000 11,500-14,000
-524D4-B series, SB No. 72-7730....................... 4,000-6,000 7,000-9,000 8,500-11,000
-524G2, G3, H, and H2 series.......................... 4,000-6,000 7,000-9,000 8,500-11,000
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(1) For discs that entered into service before 1990, remove disc
and rework as specified in paragraph (g)(2) of this AD, within five
years from the effective date of this AD, but not to exceed the
upper cyclic limit of Table 1 of this AD before rework. Discs
reworked may not exceed the manufacturer's published cyclic limit in
the time limits section of the manual.
(2) For discs that entered into service in 1990 or later, remove
disc within the cyclic life rework bands in Table 1 of this AD, or
within 17 years after the date of the disc assembly entering into
service, whichever is sooner, but not to exceed the upper cyclic
limit of Table 1 of this AD before rework. Discs reworked may not
exceed the manufacturer's published cyclic limit in the time limits
section of the manual.
(3) For disc assemblies that when new, were modified with an
application of anti-corrosion protection and re-marked to P/N
LK76036 (not previously machined) as specified by Part 1 of the
original issue of RR service bulletin (SB) No. RB.211-72-5420, dated
April 20, 1979, remove RB211-22B disc assemblies before accumulating
10,000 cycles-in-service (CIS), and remove RB211-524 disc assemblies
before accumulating 9,000 CIS.
(4) If the disc assembly date of entry into service cannot be
determined, the date of disc manufacture may be obtained from RR and
used instead.
Optional Rework of HPC Stage 3 Discs
(g) Rework HPC stage 3 disc assemblies that were removed in
paragraph (f) of this AD as follows:
(1) For disc assemblies that when new, were modified with an
application of anti-corrosion protection and re-marked to P/N
LK76036 (not previously machined) as specified by Part 1 of the
original issue of RR SB RB.211-72-5420, dated April 20, 1979, rework
disc assemblies and re-mark to either LK76034 or LK78814 using
paragraph 2.B. of the Accomplishment Instructions of RR SB No.
RB.211-72-5420, Revision 4, dated February 29, 1980. This rework
constitutes terminating action to the removal requirements in
paragraph (f) of this AD.
(2) For all other disc assemblies, rework using Paragraph 3B. of
the Accomplishment Instructions of RR SB No. RB.211-72-9434,
Revision 4, dated January 12, 2000. This rework constitutes
terminating action to the removal requirements in paragraph (f) of
this AD.
Note 1: If rework is done on disc assemblies that are removed
before the disc assembly reaches the lower life of the cyclic life
rework band in Table 1 of this AD, artificial aging of the disc to
the lower life of the rework band, at time of rework, is required.
Alternative Methods of Compliance
(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.
Material Incorporated by Reference
(i) You must use Rolls-Royce Service Bulletin No. RB.211-72-
5420, Revision 4, dated February 29, 1980, and Rolls-Royce Service
Bulletin No. RB.211-72-9434, Revision 4, dated January 12, 2000, to
perform the rework required by this AD. The Director of the Federal
Register approved the incorporation by reference of these service
bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get copies from Rolls-Royce plc, PO Box 31, Derby, England,
DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-1332-245-418.
You can review copies at the FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive Park, Burlington, MA; or
at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
Related Information
(j) Civil Aviation Authority airworthiness directive 004-01-94,
dated January 4, 2002, and RR Mandatory Service Bulletin No. RB.211-
72-9661, Revision 3, dated December 20, 1999, pertain to the subject
of this AD.
Issued in Burlington, Massachusetts, on January 8, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 04-759 Filed 1-16-04; 8:45 am]
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