AD Amdt-39-13182

[Federal Register Volume 68, Number 107 (Wednesday, June 4, 2003)]
[Rules and Regulations]
[Pages 33358-33360]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-13973]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-12-AD; Amendment 39-13182; AD 2003-10-03R1]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD) that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The existing 
AD will become effective on June 20, 2003, and requires removal from 
service of certain high pressure (HP) turbine discs before they reach 
newly established life limits. This amendment requires the same 
actions, but removes the model RB211-535E4-37 turbofan engine from the 
applicability. This revision to the existing AD is prompted by further 
data gathering by the FAA that demonstrates that the model RB211-535E4-
37 turbofan engine is not affected by machining-induced cracking within 
the currently published life of the HP turbine disc. The actions 
specified in this AD are intended to prevent machining-induced cracking 
of the HP turbine disc which could cause an uncontained HP turbine disc 
failure and damage to the airplane.

DATES: Effective June 20, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before August 4, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-12-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30

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p.m., Monday through Friday, except Federal holidays. Comments may also 
be sent via the Internet using the following address: <a href="/cdn-cgi/l/email-protection#ba8397dbd4df97dbded9d5d7d7dfd4cefadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="6e57430f000b430f0a0d0103030b001a2e080f0f40090118">[email&#160;protected]</span></a>. Comments sent via the Internet must contain the 
docket number in the subject line.
    Information regarding this action may be examined, 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 May 9, 2003, the FAA issued AD 2003-10-
03, Amendment 39-13148 (68 FR 26481, May 16, 2003), to require removal 
from service of certain HP turbine discs in RR model RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, before the 
discs reach newly established life limits. That action was prompted by 
the manufacturer's inspections and analysis of HP turbine discs that 
have accumulated high cycles. That AD will become effective on June 20, 
2003.
    The FAA is revising this amendment to remove the model RB211-535E4-
37 turbofan engine from the applicability. The FAA has received 
additional details of the engineering analysis based on field 
inspection data from the Civil Aviation Authority (CAA), which is the 
aviation authority for the U.K., and has determined that the model 
RB211-535E4-37 turbofan engine is not affected by machining-induced 
cracking within the currently published life of the HP turbine disc. 
This revised AD will be effective on June 20, 2003, in order to reduce 
the burden on operators.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the U.K. 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.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RR model RB211-535E4-B-37 and RB211-535E4-B-
75 turbofan engines of the same type design, this AD is being issued to 
prevent machining-induced cracking of the HP turbine disc which could 
cause an uncontained HP turbine disc failure and damage to the 
airplane. This AD requires removal from service of certain HP turbine 
discs before they reach newly established life limits.

Immediate Adoption of This AD

    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 unnecessary, 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, 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NE-12-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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, Safety.

Adoption of the Amendment

0
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

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. Section 39.13 is amended by removing Amendment 39-13148 (68 FR 
26481, May 16, 2003) and by adding a new airworthiness directive, 
Amendment 39-13182, to read as follows:

2003-10-03R1 Rolls-Royce plc: Amendment 39-13182. Docket No. 2002-
NE-12-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce plc (RR) model RB211-535E4-B-37 and RB211-535E4-B-75 
turbofan engines with high

[[Page 33360]]

pressure (HP) turbine disc, P/N UL10323, UL27680, and UL27681, 
installed. These engines are installed on, but not limited to Boeing 
757 and Tupolev Tu204 airplanes.

    Note 1: This 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 (d) 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: Compliance with this AD is required as indicated, 
unless already done.
    To prevent machining-induced cracking of the HP turbine disc, 
which could cause an uncontained HP turbine disc failure and damage 
to the airplane, do the following:
    (a) Remove HP turbine discs P/Ns UL27680 and UL27681 from 
service before accumulating 15,000 cycles-since-new (CSN).
    (b) Remove HP turbine discs P/N UL10323 from service before 
accumulating 14,800 CSN.
    (c) After the effective date of this AD, do not install any HP 
turbine disc P/N UL27680 or UL27681 that exceeds 15,000 CSN, or any 
HP turbine disc P/N UL10323 that exceeds 14,800 CSN.

Alternative Methods of Compliance

    (d) 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 (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    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.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Sec. Sec.  21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be done.

Effective Date

    (f) This amendment becomes effective on June 20, 2003.

    Issued in Burlington, Massachusetts, on May 29, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-13973 Filed 6-3-03; 8:45 am]
BILLING CODE 4910-13-P