[Federal Register Volume 62, Number 66 (Monday, April 7, 1997)]
[Rules and Regulations]
[Pages 16475-16477]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8474]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-ANE-56; Amendment 39-9978; AD 97-07-04]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB.211-524 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Rolls-Royce plc RB.211-524 series turbofan engines, that 
requires initial and repetitive borescope inspections of the head 
section and meterpanel assembly of the combustion liner, and 
replacement, if necessary, with serviceable parts. In addition, this AD 
allows an optional installation of a front combustion liner with a 
strengthened head section as a terminating action to the inspection

[[Page 16476]]

requirements. This amendment is prompted by reports of engine fires due 
to premature engine combustor distress. The actions specified by this 
AD are intended to prevent engine combustor liner deterioration due to 
thermal fatigue, which can result in combustor liner and case burn-
through and engine fire.

DATES: Effective June 6, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 6, 1997.

ADDRESSES: 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 Federal Aviation Administration 
(FAA), New England Region, Office of the Assistant Chief 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: Eugene Triozzi, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (617) 
238-7148, fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Rolls-Royce plc (R-R) RB.211-524 
series turbofan engines was published in the Federal Register on 
November 13, 1996 (61 FR 58147). That action proposed to require 
initial and repetitive borescope inspections of the head section and 
meterpanel assembly of the combustion liner, and replacement, if 
necessary, with serviceable parts. In addition, this AD proposed an 
optional installation of a front combustion liner with a strengthened 
head section C263 material as a terminating action to the inspection 
requirements.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. Since 
publication of the NPRM, R-R has issued Revision 3 to Service Bulletin 
No. RB.211-72-B482, dated September 27, 1996, that differs from 
Revision 2, referenced in the NPRM, by editorial changes only. This 
final rule references Revision 3 of the SB. The FAA has determined that 
air safety and the public interest require the adoption of the rule 
with the change described previously.
    There are approximately 250 engines of the affected design in the 
worldwide fleet. There are currently no domestic operators of Rolls-
Royce plc RB.211-524G or -524H series turbofan engines. The FAA 
estimates that it will take approximately 8 work hours per engine to 
accomplish the required actions, and that the average labor rate is $60 
per work hour. Based on these figures, the cost impact per engine per 
inspection is estimated to be $480.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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:

97-07-04  Rolls-Royce plc: Amendment 39-9978. Docket 95-ANE-56.

    Applicability: Rolls-Royce plc (R-R) Models RB.211-524G and -
524H turbofan engines that have not been modified in accordance with 
R-R Service Bulletin (SB) No. RB.211-72-9764, Revision 2, dated 
November 10, 1995, installed on but not limited to Boeing 747-400 
and 767-300 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 (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: Required as indicated, unless accomplished 
previously.
    To prevent engine combustor liner deterioration due to thermal 
fatigue, which can result in combustor liner and case burn-through 
and engine fire, accomplish the following:
    (a) Perform initial and repetitive borescope inspections of the 
engine combustor liner head section in accordance with the intervals 
listed in Section 1.C. Compliance (1), and the procedures described 
in Section 1.D. Action (1) of R-R SB No. RB.211-72-B482, Revision 3, 
dated September 27, 1996. Prior to further flight, remove combustors 
that do not meet the return to service criteria specified in Section 
1.E. Acceptance Limits of the SB and replace with serviceable parts.
    (b) Perform initial and repetitive borescope inspections of the 
meterpanel in accordance with the intervals listed in Section 1.C. 
Compliance (2), and the procedures described in Section 1.D. Action 
(2) of R-R SB No. RB.211-72-B482, Revision 3, dated September 27, 
1996. Prior to further flight, remove combustors that do not meet 
the return to service criteria specified in Section 1.E. Acceptance 
Limits of the SB and replace with serviceable parts.
    (c) Installation of a front combustion liner with a strengthened 
head section in C263 material in accordance with R-R SB No. RB.211-
72-9764, Revision 2, dated November 10, 1995, constitutes 
terminating action to the inspection requirements of this AD.
    (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. The 
request should be forwarded through an appropriate FAA Principal 
Maintenance Inspector, who may

[[Page 16477]]

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.

    (e) 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 requirements of this AD can be accomplished.
    (f) The actions required by this AD shall be done in accordance 
with the following R-R SBs:

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            Document No.                 Pages              Revision                          Date              
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RB.211-72-B482......................        1     3..........................  September 27, 1996.              
                                            2     2..........................  March 11, 1996.                  
                                            3     3..........................  September 27, 1996.              
                                            4     2..........................  March 11, 1996.                  
                                            5     3..........................  September 27, 1996.              
                                            6     2..........................  March 11, 1996.                  
                                          7-8     3..........................  September 27, 1996.              
                                            9     2..........................  March 11, 1996.                  
Total Pages: 9.                                                                                                 
RB.211-72-9764......................        1     2..........................  November 10, 1995.               
                                            2     Original...................  August 20, 1993.                 
                                            3     2..........................  November 10, 1995.               
                                          4-6     1..........................  August 25, 1995.                 
                                         7-30     Original...................  August 20, 1993.                 
Supplement..........................        1     Original...................  August 20, 1993.                 
Total Pages: 31.                                                                                                
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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 Assistant Chief 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.
    (g) This amendment becomes effective on June 6, 1997.
    Issued in Burlington, Massachusetts, on March 26, 1997.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 97-8474 Filed 4-4-97; 8:45 am]
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