[Federal Register Volume 65, Number 52 (Thursday, March 16, 2000)]
[Rules and Regulations]
[Pages 14207-14209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-5891]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-02-AD; Amendment 39-11622; AD 2000-05-12]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 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 certain Rolls-Royce plc RB211-524 series turbofan 
engines. This action requires initial and repetitive ultrasonic 
inspections for cracks in fan blade dovetail roots, and, if necessary, 
replacement with serviceable parts. This action also provides the 
options of installing improved design fan blades or reworking current 
fan blades to the improved configuration as terminating action for the 
inspections. This amendment is prompted by reports of fan blade 
failures due to dovetail root cracks. The actions specified in this AD 
are intended to prevent possible multiple fan blade failures, which 
could result in an uncontained engine failure and damage to the 
aircraft.

DATES: Effective March 31, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 31, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before May 15, 2000.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-02-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299. Comments may also be sent via the Internet 
using the following address: ``[email protected]''. 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 plc, PO Box 31, Derby, England; telephone: International 
Access Code 011, Country Code 44, 1332-249428, fax International Access 
Code 011, Country Code 44, 1332-249223. 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 certain Rolls-Royce plc (R-R) RB211-524 series 
turbofan engines. The CAA received reports of three fan blade failures 
to date. Subsequent inspections of the dovetail root area on other fan 
blades revealed the existence of dovetail root cracks in the same 
region as the failed blades. This condition, if not corrected, could 
result in possible multiple fan blade failures, which could result in 
an uncontained engine failure and damage to the aircraft

Service Information

    R-R has issued Mandatory Service Bulletin (SB) No. RB.211-72-C818, 
Revision 2, dated October 8, 1999, that specifies procedures for 
ultrasonic inspections for cracks in fan blade dovetail roots and 
provides rejection criteria. The CAA classified this SB as mandatory 
and issued airworthiness directive (AD) 007-10-99 in order to assure 
the airworthiness of these engines in the UK.
    In addition, R-R has issued SB RB.211-72-C891, dated February 2, 
2000, that describes procedures for installing improved design fan 
blades or

[[Page 14208]]

reworking current fan blades to the improved configuration.

Bilateral Airworthiness Agreement

    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.

Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design, this AD 
requires initial and repetitive ultrasonic inspections for cracks in 
fan blade dovetail roots, and, if necessary, replacement of cracked fan 
blades with serviceable parts. This AD also provides the options of 
installing improved design fan blades or reworking current fan blades 
to the improved configuration as terminating action for the 
inspections. The improved design fan blades are undercut along the 
entire length of the blade root block and the blade root flanks are now 
grit blasted. In addition, the dry film lubricant is applied in an 
improved adhesive manner and the thickness of both the front and rear 
chocking pads and stop lug pin assembly has been reduced.

Immediate Adoption

    There are currently no domestic operators of this engine model. 
Accordingly, a situation exists that allows the immediate adoption of 
this regulation. Notice and opportunity for prior public comment hereon 
are impracticable, and 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 
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, 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 2000-NE-02-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 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:

2000-05-12  Rolls-Royce plc: Amendment 39-11622. Docket 2000-NE-02-
AD.

    Applicability: Rolls-Royce plc (R-R) Models RB211-524G2-19, 
RB211-524G3-19, RB211-524H2-19, RB211-524G2-T-19, RB211-524G3-T-19, 
RB211-524H2-T-19, and RB211-524H-36 turbofan engines, with fan 
blades, part numbers (P/Ns) UL36245, UL38009, UL38052, or UL38628, 
installed. These engines are installed on but not limited to Boeing 
747-400 series and 767 series airplanes.

    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 (c) 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 possible multiple fan blade failures, which could 
result in an uncontained engine failure and damage to the aircraft, 
accomplish the following:

Ultrasonic Inspections

    (a) Ultrasonically inspect the dovetail roots of fan blades, P/
Ns UL36245, UL38009, UL38052, and UL38628, for cracks as follows:

Initial Inspection

    (1) Initially inspect at the latest of:
    (i) before accumulating 2,050 total fan blade part cycles-since-
new.
    (ii) 50 fan blade cycles-in-service (CIS) after the effective 
date of this AD.
    (iii) 200 fan blade CIS since last inspection.

Service Bulletin

    (2) Inspect and determine rejection status in accordance with 
the following paragraphs

[[Page 14209]]

of R-R Mandatory Service Bulletin (SB) RB.211-72-C818, Revision 2, 
dated October 8, 1999:
    (i) Compliance section C, page 2.
    (ii) Accomplishment Instructions section, items A through and 
including B(6), pages 5 and 6.
    (iii) Acceptance criteria section, Appendix 1 (4), items A and 
B, page 9.

Earlier Versions of Service Bulletin

    (3) Initial inspections accomplished using the original issue of 
R-R SB RB.211-72-C818, dated August 6, 1999, or Revision 1, dated 
August 20, 1999, are acceptable.

Repetitive Inspections

    (4) Thereafter, inspect at intervals not to exceed 200 CIS since 
last inspection in accordance with R-R Mandatory RB.211-72-C818, 
Revision 2, dated October 8, 1999.

Cracked Parts

    (5) Prior to further flight, remove from service cracked fan 
blades and replace with serviceable parts in accordance with R-R 
Mandatory RB.211-72-C818, Revision 2, dated October 8, 1999.

Optional Terminating Action

    (b) Accomplishment of either of the following actions 
constitutes terminating action to the inspections required by 
paragraph (a) of this AD:
    (1) Remove from service fan blades, P/Ns UL36245, UL38009, 
UL38052, and UL38628, and replace with serviceable fan blades with 
P/Ns other than P/Ns UL36245, UL38009, UL38052, and UL38628, or
    (2) Rework fan blades to the improved configuration and mark the 
reworked fan blades with P/Ns FW12018, FW12019, FW12020, or FW12021, 
in accordance with the Accomplishment Instructions of R-R SB RB.211-
72-C891, dated February 2, 2000.

Alternative Methods of Compliance

    (c) 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 AD, if any, may be 
obtained from the Engine Certification Office.

Ferry Flights

    (d) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (e) The actions required by this AD shall be performed in 
accordance with the R-R Mandatory SB RB.211-72-C818, Revision 2, 
dated October 8, 1999, and SB RB.211-72-C891, dated February 2, 
2000. 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 plc, PO Box 31, 
Derby, England; telephone: International Access Code 011, Country 
Code 44, 1332-249428, fax International Access Code 011, Country 
Code 44, 1332-249223. 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.
    (f) This amendment becomes effective on March 31, 2000.

    Issued in Burlington, Massachusetts, on March 6, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-5891 Filed 3-15-00; 8:45 am]
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