[Federal Register Volume 63, Number 183 (Tuesday, September 22, 1998)]
[Rules and Regulations]
[Pages 50484-50485]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25006]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-33-AD; Amendment 39-10762; AD 98-18-21]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce, plc RB211 Trent 800 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan
engines. This action requires initial and repetitive ultrasonic
inspections of fan blade roots for cracks, and replacement, if
necessary, with serviceable parts. This amendment is prompted by
reports of multiple fan blade root cracks in several factory test
engines. The actions specified in this AD are intended to prevent fan
blade failure, which could result in multiple fan blade release,
uncontained engine failure, and possible damage to the aircraft.
DATES: Effective October 7, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 7, 1998.
Comments for inclusion in the Rules Docket must be received on or
before November 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-33-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD may be obtained from
Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis,
IN 46241; telephone (317) 230-3995, fax (317) 230-4743. This
information may be examined 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: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7176, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom (UK), recently
notified the Federal Aviation Administration (FAA) that an unsafe
condition may exist on Rolls-Royce, plc (R-R) RB211 Trent 875-17, RB211
Trent 877-17, RB211 Trent 884-17, RB211 Trent 892-17, and RB211 Trent
892B-17 series turbofan engines. The CAA advises that during inspection
of 4 sets of fan blades from 4 separate factory test engines, including
flight test, cracks were discovered in several of the fan blade root
sections. Two engine sets contained multiple numbers of fan blades
exhibiting blade root cracks and two engine sets contained one fan
blade each exhibiting blade root cracks. The investigation revealed
that the cracks are caused by higher than expected stresses in the fan
blade root section at high fan speeds. This condition, if not detected,
could result in fan blade failure which could result in multiple fan
blade release, uncontained engine failure, and possible damage to the
aircraft.
There are currently no affected engines operated on aircraft of
U.S. registry. This AD, then, is necessary to require accomplishment of
the required actions for engines installed on aircraft currently of
foreign registry that may someday be imported into the U.S.
Accordingly, the FAA has determined that notice and prior opportunity
for comment are unnecessary and good cause exists for making this
amendment effective in less than 30 days.
R-R has issued Service Bulletin (SB) No. RB.211-72-C445, Revision
2, dated July 3, 1998, that specifies procedures for inspections of fan
blade roots for cracks. The CAA classified this SB as mandatory and
issued AD 003-04-98 in order to assure the airworthiness of these
engines in the UK.
This engine model is manufactured in the UK and is 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. Pursuant to this
bilateral airworthiness agreement, the CAA has kept the FAA informed of
the situation described above. The FAA has 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design registered in
the United States, the AD requires initial and repetitive ultrasonic
inspections of fan blade roots for cracks, and replacement, if
necessary, with serviceable parts. This AD is considered interim
action, as future rulemaking may be forthcoming that would require
installing redesigned fan blades. The actions would be required to be
accomplished in accordance with the SB described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic,
[[Page 50485]]
environmental, and energy aspects of the rule that might suggest a need
to modify the rule. All comments submitted will be available, both
before and after the closing date for comments, in the Rules Docket for
examination by interested persons. A report that summarizes each FAA-
public contact concerned with the substance of this AD will be filed in
the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-ANE-33-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to 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
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. Section 39.13 is amended by adding the following new
airworthiness directive:
98-18-21 Rolls-Royce, plc: Amendment 39-10762. Docket 98-ANE-33-
AD.
Applicability: Rolls-Royce, plc (R-R) RB211 Trent 875, RB211
Trent 877, RB211 Trent 884, RB211 Trent 892, and RB211 Trent 892B
series turbofan engines, with fan blades, part numbers FK 23750, FK
25975, FK 25548, and FK 26757, installed. These engines are
installed on but not limited to Boeing 777 series aircraft.
Note 1: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request
approval for an alternative method of compliance in accordance with
paragraph (b) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fan blade failure, which could result in multiple fan
blade release, uncontained engine failure, and possible damage to
the aircraft, accomplish the following:
(a) Perform initial and repetitive inspections of fan blade
roots for cracks, in accordance with R-R Service Bulletin (SB) No.
RB.211-72-C445, Revision 2, dated July 3, 1998, as follows:
(1) For Trent 875 series engines, as follows:
(i) Initially inspect prior to accumulating 3,000 cycles since
new (CSN).
(ii) Thereafter, inspect at intervals not to exceed 500 cycles
in service (CIS) since last inspection.
(2) For Trent 877 series engines, as follows:
(i) Initially inspect prior to accumulating 2,500 CSN.
(ii) Thereafter, inspect at intervals not to exceed 500 CIS
since last inspection.
(3) For Trent 884 series engines, as follows:
(i) Initially inspect prior to accumulating 1,500 CSN.
(ii) Thereafter, inspect at intervals not to exceed 500 CIS
since last inspection.
(4) For Trent 892 and 892B series engines, as follows:
(i) Initially inspect prior to accumulating 1,000 CSN.
(ii) Thereafter, inspect at intervals not to exceed 300 CIS
since last inspection.
(5) Remove from service cracked fan blades and replace with
serviceable parts.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Engine Certification Office.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(d) The actions required by this AD shall be performed in
accordance with the following R-R SB:
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Document No. Pages Revision Date
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RB.211-72-C445................. 1-8 2 July 3, 1998.
Appendix 1..................... 1-4 2 July 3, 1998.
Appendix 2..................... 1-4 2 July 3, 1998.
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Total pages: 16.
This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Copies may be obtained from Rolls-Royce North America, Inc., 2001 South
Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317)
230-4743. Copies may be inspected 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.
(e) This amendment becomes effective on October 7, 1998.
Issued in Burlington, Massachusetts, on September 11, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-25006 Filed 9-21-98; 8:45 am]
BILLING CODE 4910-13-P
