[Federal Register Volume 63, Number 87 (Wednesday, May 6, 1998)]
[Rules and Regulations]
[Pages 24911-24912]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11437]



 ========================================================================
 Rules and Regulations
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains regulatory documents 
 having general applicability and legal effect, most of which are keyed 
 to and codified in the Code of Federal Regulations, which is published 
 under 50 titles pursuant to 44 U.S.C. 1510.
 
 The Code of Federal Regulations is sold by the Superintendent of Documents. 
 Prices of new books are listed in the first FEDERAL REGISTER issue of each 
 week.
 
 ========================================================================
 

  Federal Register / Vol. 63, No. 87 / Wednesday, May 6, 1998 / Rules 
and Regulations  

[[Page 24911]]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-09-AD; Amendment 39-10508; AD 98-09-27]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce, plc RB211 Trent 768 and 
772 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Rolls-Royce, plc RB211 Trent 768 and 772 series 
turbofan engines. This action requires initial and repetitive visual 
inspections of thrust reverser hinge lugs and attachment ribs for 
cracks, and, if necessary, removal from service and replacement with 
serviceable parts. This amendment is prompted by aircraft certification 
testing which revealed that stresses on the thrust reverser hinge were 
higher than had been anticipated during engine certification. The 
actions specified in this AD are intended to prevent thrust reverser 
hinge failure, possibly resulting in liberation of the thrust reverser 
cowl duct from the engine nacelle, which could result in impact damage 
to other sections of the aircraft.

DATES: Effective May 21, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 21, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before July 6, 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-09-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``9-ad-
[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 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 768 and 772 series turbofan engines. The CAA advises 
that test measurements of the pylon to thrust reverser cowl duct hinge 
loads revealed lower than expected hinge lug load carrying capability. 
In the event of failure of one of the thrust reverser cowl duct hinges, 
there is a reduced fatigue life capability on the adjacent hinge. This 
could lead to premature failure of the thrust reverser cowl duct 
hinges, resulting in liberation of the cowl duct from 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. This condition, if not corrected, could result in 
thrust reverser hinge failure, possibly resulting in liberation of the 
thrust reverser cowl duct from the engine nacelle, which could result 
in impact damage to other sections of the aircraft.
    R-R has issued Service Bulletin (SB) No. RB.211-78-B115, Revision 
1, dated March 14, 1997, that specifies procedures for visual 
inspections of thrust reverser hinge lugs and attachment ribs for 
cracks. The CAA classified this SB as mandatory and issued AD 008-03-97 
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 
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, this AD requires initial and repetitive visual 
inspections of thrust reverser hinge lugs and attachment ribs for 
cracks, and, if necessary, removal from service and replacement with 
serviceable parts. 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

[[Page 24912]]

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-09-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:

98-09-27  Rolls-Royce, plc: Amendment 39-10508. Docket 98-ANE-09-AD.

    Applicability: Rolls-Royce, plc (R-R) RB211 Trent 768 and 772 
series turbofan engines, installed on but not limited to the Airbus 
A330-341 and A330-342 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 thrust reverser hinge failure, possibly resulting in 
liberation of the thrust reverser cowl duct from the engine nacelle, 
which could result in impact damage to other sections of the 
aircraft, accomplish the following:
    (a) Perform initial and repetitive visual inspections of thrust 
reverser hinge lugs and attachment ribs for cracks, and, if 
necessary, remove from service and replace with serviceable parts, 
in accordance with R-R Service Bulletin (SB) No. RB.211-78-B115, 
Revision 1, dated March 14, 1997, as follows:
    (1) Perform the initial inspection at the earlier of the 
following:
    (i) 250 hours time in service (TIS) after the effective date of 
this AD; or
    (ii) 1,200 flight cycles since new (CSN).
    (2) Thereafter, perform visual inspections at intervals not to 
exceed 1,200 flight cycles in service (CIS) since last inspection.
    (3) If thrust reverser hinge lugs or attachment ribs are found 
cracked, remove from service and replace with serviceable parts, in 
accordance with R-R Service Bulletin (SB) No. RB.211-78-B115, 
Revision 1, dated March 14, 1997.
    (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 inspection 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:

----------------------------------------------------------------------------------------------------------------
                 Document No.                     Pages     Revision                     Date                   
----------------------------------------------------------------------------------------------------------------
RB.211-78-B115................................        1-6          1  March 14, 1997.                           
      Total pages: 6.                                                                                           
----------------------------------------------------------------------------------------------------------------

    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 May 21, 1998.

    Issued in Burlington, Massachusetts, on April 23, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11437 Filed 5-5-98; 8:45 am]
BILLING CODE 4910-13-U