[Federal Register Volume 68, Number 17 (Monday, January 27, 2003)]
[Proposed Rules]
[Pages 3836-3837]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-1676]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-19-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 875, 877, 
884, 892, 892B, and 895 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a 
new airworthiness directive (AD) that is applicable to Rolls-Royce plc 
(RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan 
engines. This proposal would require initial and repetitive visual 
inspections of the intermediate pressure (IP) compressor rear stubshaft 
and IP turbine shaft for load-bearing spline flank wear, and 
replacement of these shafts if necessary. This proposal is prompted by 
reports of IP compressor rear stubshaft and IP turbine shaft load-
bearing spline flank wear, revealed at inspection during overhaul. The 
actions specified by the proposed AD are intended to prevent the loss 
of drive between the IP turbine and the IP compressor, which could 
result in a turbine rotor overspeed condition, possible uncontained 
engine failure, and damage to the airplane.

DATES: Comments must be received by March 28, 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-19-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 p.m., Monday 
through Friday, except Federal holidays. 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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-19-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2002-NE-19-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom (U.K.), notified the FAA that an 
unsafe condition may exist on RR RB211 Trent 875, 877, 884, 892, 892B, 
and 895 series turbofan engines. The CAA advises that twelve reports 
have been received of overhaul inspections revealing unacceptable 
levels of flank wear on IP compressor rear stubshaft splines and IP 
turbine shaft splines. This unacceptable wear is attributed to the 
current design air/oil mist lubrication method used for the splines. 
Excessive wear can lead to loss of spline drive between the IP 
compressor and the IP turbine shaft, resulting in IP turbine rotor 
overspeed and possible uncontained engine failure.

Pending Optional Terminating Action

    RR has informed the FAA that they are planning an optional 
terminating action for the repetitive inspections specified in 
paragraph (a) of this proposal. This optional terminating action will 
incorporate improved modules with new identities. RR is planning to 
introduce information in the first quarter of 2003 on modifying 
affected modules to new module identities in RR Major Modification 
Bulletin No. 72-D495.

Bilateral Agreement Information

    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.

Proposed Requirements of this AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RR RB211 Trent 875, 877, 884, 892, 892B, and 
895 series turbofan engines of the same type design, the proposed AD 
would require initial and repetitive visual inspections of the IP 
compressor rear stubshaft and IP turbine shaft for load-bearing spline 
flank wear, and replacement of these shafts if necessary.

Economic Analysis

    There are approximately 350 engines of the affected design in the 
worldwide fleet. The FAA estimates that 102 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD. The 
FAA also estimates that it would take approximately 0.5 work hour per 
engine to accomplish the proposed inspection for parts determined not 
worn, and an additional 1.5 work hours per engine for parts determined 
worn that would require further inspection. The average labor rate is 
$60 per work hour. Based on

[[Page 3837]]

these figures, the total cost of the proposed AD to U.S. operators is 
estimated to be $12,240.00.

Regulatory Analysis

    This proposed 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 proposed rule.
    For the reasons discussed above, I certify that this proposed 
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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Rolls-Royce plc: Docket No. 2002-NE-19-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce plc RB211 Trent 875, 877, 884, 892, 892B, and 895 
series turbofan engines. These engines are installed on, but not 
limited to Boeing 777 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 (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: Compliance with this AD is required as indicated, 
unless already done.
    To prevent the loss of drive between the intermediate pressure 
(IP) turbine and the IP compressor, which could result in a turbine 
rotor overspeed condition, possible uncontained engine failure, and 
damage to the airplane, do the following:
    (a) At or before the accumulation of 4,500 cycles-in-service 
after the effective date of this AD, remove the 05 module 
(consisting of the IP turbine and low pressure turbine) and do the 
following:
    (1) Visually inspect the load-bearing splines of the IP turbine 
shaft for flank wear.
    (2) If flank wear is 0.001 inch or less, return the 05 module to 
service and repetitively inspect the splines within 4,500 cycles-
since-last-inspection, as specified in paragraph (a) of this AD.
    (3) If flank wear is between 0.001 inch and 0.005 inch, also 
visually inspect the load-bearing splines of the IP compressor rear 
stubshaft for flank wear.
    (4) Replace any shaft with load-bearing spline wear over 0.005 
inch.
    (5) If flank wear on load-bearing splines is between 0.001 inch 
and 0.005 inch, return the 05 module to service and repetitively 
inspect the splines within 2,000 cycles-since-last-inspection, as 
specified in paragraph (a) of this AD. Information on inspection of 
these splines can be found in Rolls-Royce Mandatory Service Bulletin 
RB.211-72-D339, dated September 14, 2001.

Alternative Methods of Compliance

    (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 (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 ECO.

Special Flight Permits

    (c) 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.

    Note 3: The subject of this AD is addressed in CAA airworthiness 
directive 003-09-2001, dated September 14, 2001.


    Issued in Burlington, Massachusetts, on January 16, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-1676 Filed 1-24-03; 8:45 am]
BILLING CODE 4910-13-P