AD Amdt-39-10754

[Federal Register Volume 63, Number 179 (Wednesday, September 16, 1998)]
[Rules and Regulations]
[Pages 49416-49418]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-24645]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-10-AD; Amendment 39-10754; AD 98-19-12]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce, plc RB211 Trent 700 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 700 series turbofan 
engines. This action requires repositioning of the oil metering jet up 
into the oil distributor within the bevel gearshaft, followed by 
repetitive inspections of the Magnetic Chip Detector (MCD). Evidence of 
driving bevel gearshaft ball bearing failure requires replacement of 
the Step Aside Gearbox (SAGB). This amendment is prompted by reports of 
uncommanded engine rundowns caused by failure of the SAGB driving bevel 
gearshaft ball bearing due to oil starvation. This causes a loss of 
drive to the external gearbox and accessories, resulting in an inflight 
engine shutdown. The actions specified in this AD are intended to 
prevent inflight engine shutdowns caused by SAGB driving bevel 
gearshaft ball bearing failure.

DATES: Effective October 1, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 1, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before November 16, 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-10-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#97aebaf6f3ba9df2f9f0fef9f2e7e5f8e7d7f1f6f6b9f3f8e3b9f0f8e1">9-ad-
<span class="__cf_email__" data-cfemail="a1c4cfc6c8cfc4d1d3ced1e1c7c0c08fc5ced58fc6ced7">[email&#160;protected]</span></a>''. 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 FAA that an unsafe condition 
may exist on Rolls-Royce, plc (R-R) RB211 Trent 700 series turbofan 
engines. The CAA advises that they have received reports of 4 
uncommanded engine rundowns caused by failure of the Step Aside Gearbox 
(SAGB) driving bevel gearshaft ball bearing and loss of drive to the 
external gearbox and accessories, resulting in an inflight shutdown. 
The

[[Page 49417]]

investigation revealed that the ball bearing failures were due to 
inadequate oil flow to the bearing as a result of movement of the oil 
jet due to windage affects inside the gearbox. 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. 
This condition, if not corrected, could result in inflight engine 
shutdowns caused by SAGB driving bevel gearshaft ball bearing failure.
    R-R has issued Service Bulletin (SB) No. RB.211-72-C270, dated June 
1, 1997, that specifies procedures for repositioning the oil metering 
jet up into the oil distributor within the bevel gearshaft, and SB No. 
RB.211-79-C135, dated July 4, 1997, that specifies procedures for 
inspections of the Magnetic Chip Detector for evidence of SAGB driving 
bevel gearshaft ball bearing failure. The CAA classified these SBs as 
mandatory and issued ADs 001-05-97 and 002-06-97 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 
Sec. 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, this AD requires, prior to further flight, 
repositioning of the oil metering jet up into the oil distributor 
within the bevel gearshaft. In addition, this AD requires repetitive 
inspections of the Magnetic Chip Detector at intervals between 60 hours 
minimum time in service (TIS) and 130 hours maximum TIS since last 
inspection. If evidence of a bearing failure is found, this AD requires 
replacement of the Step Aside Gearbox with a serviceable part. The 
actions would be required to be accomplished in accordance with the SBs 
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, 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-10-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:

98-19-12  Rolls-Royce, plc: Amendment 39-10754. Docket 98-ANE-10-AD.

    Applicability: Rolls-Royce, plc (R-R) RB211 Trent 700 series 
turbofan engines, installed on but not limited to Airbus A330 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 (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.

[[Page 49418]]

    To prevent inflight engine shutdowns caused by Step Aside 
Gearbox (SAGB) driving bevel gearshaft ball bearing failure, 
accomplish the following:
    (a) Prior to further flight, reposition the oil metering jet up 
into the oil distributor within the bevel gearshaft in accordance 
with R-R Service Bulletin (SB) No. RB.211-72-C270, dated June 1, 
1997.
    (b) Perform initial and repetitive inspections of the Magnetic 
Chip Detector for evidence of SAGB driving bevel gearshaft ball 
bearing failure in accordance with R-R SB No. RB.211-79-C135, dated 
July 4, 1997, as follows:
    (1) Perform the initial inspection in accordance with R-R SB No. 
RB.211-79-C135, within 60 hours time in service (TIS) after 
repositioning the oil metering jet up into the oil distributor 
within the bevel gearshaft in accordance with R-R Service Bulletin 
(SB) No. RB.211-72-C270.
    (2) Thereafter, inspect at intervals between 60 hours minimum 
TIS and 130 hours maximum TIS since last inspection.
    (3) If evidence of a SAGB driving bevel gearshaft ball bearing 
failure is found, replace the SAGB with a serviceable part.
    (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 airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

    (d) Special flight permits may be issued in accordance with 
Secs. 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 inspection requirements of this AD can be accomplished.
    (e) The actions required by this AD shall be performed in 
accordance with the following R-R SBs:

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            Document  No.              Pages              Date          
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RB.211-72-C270......................      1-7  June 1, 1997.            
    Total pages: 7.                                                     
RB.211-79-C135......................      1-2  July 4, 1997.            
    Total pages: 2.                                                     
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    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.
    (f) This amendment becomes effective on October 1, 1998.

    Issued in Burlington, Massachusetts, on September 8, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 98-24645 Filed 9-15-98; 8:45 am]
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