[Federal Register: January 27, 2005 (Volume 70, Number 17)]
[Rules and Regulations]
[Page 3863-3867]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27ja05-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-13-AD; Amendment 39-13950; AD 2005-02-05]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and
RB211-535E4-B-75 series turbofan engines. That AD currently requires
initial and repetitive ultrasonic inspections of installed LPC fan
blade roots on-wing and during overhaul using a surface wave ultrasonic
probe, and relubrication, according to accumulated life cycles. That AD
also adds the application of Metco 58 blade root coating as an optional
terminating action. This AD requires the same actions, but changes the
reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from
Revision 3 to Revision 4. This AD results from RR issuing MSB No.
RB.211-72-C879, Revision 4, which contains revised Accomplishment
Instructions and consumable materials list. We are
[[Page 3864]]
issuing this AD to detect cracks in low pressure compressor (LPC) fan
blade roots, which if not detected, could lead to uncontained multiple
fan blade failure, and damage to the airplane.
DATES: Effective February 11, 2005. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of February 11, 2005.
We must receive any comments on this AD by March 28, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2000-NE-13-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information referenced in this AD from
Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-
1332-242-424; fax: 011-44-1332-249-936.
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.
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: On June 13, 2003, we issued AD 2003-12-15,
Amendment 39-13200 (68 FR 37735, June 25, 2003). That AD requires
initial and repetitive ultrasonic inspections of installed LPC fan
blade roots on-wing and during overhaul using a surface wave ultrasonic
probe, and relubrication, according to accumulated life cycles. That AD
also introduces an alternative technique to ultrasonically inspect
installed fan blades on-wing using a surface wave ultrasonic probe.
Also, that AD adds the application of Metco 58 blade root coating as an
optional terminating action. That AD was the result of the discovery of
cracks on LPC fan blade roots during an engine overhaul. That
condition, if not corrected, could result in uncontained multiple fan
blade failure, and damage to the airplane.
Actions Since AD 2003-12-15 Was Issued
Since AD 2003-12-15 was issued, the Civil Aviation Authority (CAA),
which is the airworthiness authority for the United Kingdom (UK),
notified us that Rolls-Royce plc has updated MSB No. RB.211-72-C879,
Revision 3, dated October 3, 2002, to Revision 4, dated April 2, 2004,
for RR RB211 series turbofan engines. The CAA advises that Revision 4
of the MSB contains revised Accomplishment Instructions and consumable
materials list.
Special Flight Permits Paragraph Removed
Paragraph (h) of the current AD, AD 2003-12-15, contains a
paragraph pertaining to special flight permits. Even though this final
rule does not contain a similar paragraph, we have made no changes with
regard to the use of special flight permits to operate the airplane to
a repair facility to do the work required by this AD. In July 2002, we
published a new part 39 that contains a general authority regarding
special flight permits and airworthiness directives; see Docket No.
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus,
when we now supersede ADs we will not include a specific paragraph on
special flight permits unless we want to limit the use of that general
authority granted in section 39.23.
Relevant Service Information
We have reviewed and approved the technical contents of RR MSB No.
RB.211-72-C879, Revision 4, dated April 2, 2004. That MSB describes
procedures for ultrasonic inspection of high cyclic life blades on-wing
with either the LPC fan blades in place or removed from the LPC. The
CAA classified the original issue of the service bulletin as mandatory
and issued AD 002-01-2000 in order to ensure the airworthiness of these
RR engines in the UK.
Bilateral Airworthiness Agreement
These engine models are manufactured in the U.K. and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Under this bilateral
airworthiness agreement, the CAA has kept the FAA informed of the
situation described above. We have examined the findings of the CAA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
FAA's Determination and Requirements of This 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. Therefore, we are issuing this AD, which
requires initial and repetitive ultrasonic inspection of installed LPC
fan blade roots on-wing and during overhaul using a surface wave
ultrasonic probe, and relubrication, according to accumulated life
cycles. This AD also maintains the application of Metco 58 blade root
coating as an optional terminating action. You must use the service
information described previously to perform the actions required by
this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are unnecessary, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-13-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 rule
that might suggest a need to modify it. If a person contacts us
verbally, and that contact relates to a substantive part of this AD, we
will summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend the 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.
[[Page 3865]]
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 the 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. 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. 2000-NE-13-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 part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13200 (68 FR
37735, June 25, 2003), and by adding a new airworthiness directive,
Amendment 39-13950, to read as follows:
2005-02-05 Rolls-Royce plc: Amendment 39-13950. Docket No. 2000-NE-
13-AD. Supersedes AD 2003-12-15, Amendment 39-13200.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
11, 2005.
Affected ADs
(b) This AD supersedes AD 2003-12-15, Amendment 39-13200.
Applicability
(c) This AD applies to Rolls-Royce (RR) plc RB211-535E4-37,
RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines with
low pressure compressor (LPC) fan blades with the part numbers (P/
Ns) listed in Table 1 of this AD. These engines are installed on,
but not limited to, Boeing 757 and Tupolev Tu204 series airplanes.
Table 1 follows:
Table 1.--Applicable LPC Fan Blade P/Ns
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UL16135 UL28602
UL16171 UL29511
UL16182 UL29556
UL19643 UL30817
UL20044 UL30819
UL20132 UL30933
UL20616 UL30935
UL21345 UL33707
UL22286 UL33709
UL23122 UL36992
UL24525 UL37090
UL24528 UL37272
UL24530 UL37274
UL24532 UL37276
UL24534 UL37278
UL27992 UL38029
UL28601 UL38032
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Unsafe Condition
(d) This AD results from RR issuing Mandatory Service Bulletin
(MSB) No. RB.211-72-C879, Revision 4, which contains revised
Accomplishment Instructions and consumable materials list. We are
issuing this AD to detect cracks in low pressure compressor (LPC)
fan blade roots, which if not detected, could lead to uncontained
multiple fan blade failure, and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
(f) If you have a full set of fan blades, modified using RR
Service Bulletin No. RB.211-72-C946, Revision 2, dated September 26,
2002, that can be identified by a blue triangle etched on the blade
airfoil suction surface close to the leading edge tip of each blade,
no further action is required.
(g) On RB211-535E4 engines, operated to Flight Profile A,
ultrasonically inspect, and if required, relubricate using the
following Table 2:
Table 2.--RB211-535E4 Flight Profile A
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Initial
inspection
Engine location within cycles- Type action In accordance with Repeat inspection
since-new within (CSN)
(CSN)
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(1) On-wing................ 17,350 (i) Root Probe, RB.211-72-C879 Revision 1,400
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 1,150
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 17,350 Root Probe, inspect RB.211-72-C879 Revision 1,400
and relubricate. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
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(h) On RB211-535E4 engines, operated to Flight Profile B,
ultrasonically inspect, and if required, relubricate using the
following Table 3:
[[Page 3866]]
Table 3.--RB211-535E4 Flight Profile B
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Initial
Engine location inspection Type action In accordance with Repeat inspection
within (CSN) within (CSN)
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(1) On-wing................ 12,350 (i) Root Probe, RB.211-72-C879 Revision 850
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 700
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 12,350 Root Probe, inspect RB.211-72-C879 Revision 850
and relubricate. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
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(i) On RB211-535E4 engines, operated to combined Flight Profile
A and B, ultrasonically inspect, and if required, relubricate using
the following Table 4:
Table 4.--RB211-535E4 Flight Profile A and B
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Initial inspection Repeat inspection within
Engine location within (CSN) Type action In accordance with (CSN)
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(1) On-wing........... 65% hard life (To (i) Root Probe, RB.211-72-C879 As current flight
calculate, see inspect and Revision 4, 3.A.(1) profile.
Compliance Section relubricate, OR through 3.A.(7),
1.C(4)). dated April 2, 2004.
..................... (ii) Wave Probe. RB.211-72-C879 As current flight
Revision 4, 3.B.(1) profile.
through 3.B.(7),
dated April 2, 2004.
(2) In Shop........... 65% hard life (To Root Probe, RB.211-72-C879 As current flight
calculate, see inspect and Revision 4, 3.C.(1) profile.
Compliance Section relubricate. through 3.C.(4),
1.C.(4)). dated April 2, 2004.
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(j) Fan blades that have been operated within RB211-535E4 Flight
Profile A and B will have final life as defined in the Time Limits
Manual. See References Section 1.G.(3), of MSB RB.211-72-C879,
Revision 4, dated April 2, 2004.
(k) On RB211-535E4-B engines, ultrasonically inspect, and if
required, relubricate using the following Table 5:
Table 5.--RB211-535E4-B
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Initial
Engine location inspection Type action In accordance with Repeat inspection
within (CSN) within (CSN)
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(1) On-wing................ 17,000 (i) Root Probe, RB.211-72-C879 Revision 1,200
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 1,000
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 17,000 Root Probe, inspect RB.211-72-C879 Revision 1,200
and relubricate.. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
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Optional Terminating Action
(l) Application of Metco 58 blade root coating using RR SB No.
RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes
terminating action to the repetitive inspection requirements
specified in paragraphs (g), (h), (i), and (k) of this AD.
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.
Previous Credit
(n) Previous credit is allowed for initial and repetitive
inspections performed using AD 2003-12-15 (Amendment 39-13200, 68 FR
37735, June 25, 2003) and RR MSB No. RB.211-72-C879, Revision 3,
dated October 9, 2002.
Material Incorporated by Reference
(o) You must use Rolls-Royce Mandatory Service Bulletin No.
RB.211-72-C879, Revision 4, dated April 2, 2004, to perform the
inspections and relubrication 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, PO Box 31, Derby,
England, DE248BJ; telephone: 011-44-1332-242-424; fax: 011-44-1332-
249-936. You may review copies at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA; or on the Internet at http://dms.dot.gov; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Related Information
(p) CAA airworthiness directive AD 002-01-2000, dated October 9,
2002, also addresses the subject of this AD.
[[Page 3867]]
Issued in Burlington, Massachusetts, on January 18, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-1384 Filed 1-26-05; 8:45 am]
BILLING CODE 4910-13-P