[Federal Register Volume 66, Number 23 (Friday, February 2, 2001)]
[Rules and Regulations]
[Pages 8752-8754]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-2609]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-54-AD; Amendment 39-12098; AD 2000-25-51]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland GmbH (Formerly 
BMW Rolls-Royce GmbH) Model BR700-715A1-30, BR700-715B1-30, and BR700-
715C1-30 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2000-25-51 that was sent 
previously to all known U.S. owners and operators of Rolls-Royce 
Deutschland GmbH (formerly BMW Rolls-Royce GmbH) model BR700-715A1-30, 
BR700-715B1-30, and BR700-715C1-30 turbofan engines. This action 
requires that certain high pressure turbine (HPT) stage 1 disks, part 
numbers (P/N's) BRH20009, BRH20010, BRH12167, BRH12168, BRH12466, and 
BRH12467; and stage 2 disks, P/N's BRH19349 and BRH19350, be removed 
before exceeding the new reduced cyclic limit, and replaced with a 
serviceable disk. This amendment is prompted by a reduction of the life 
limit for several high pressure turbine (HPT) stage 1 and stage 2 
disks. The actions specified in this AD are intended to prevent an 
uncontained failure of the HPT stage 1 or stage 2 disk due to exceeded 
life-cycle limits.

DATES: Effective February 20, 2001, to all owners and operators except 
those to whom it was made immediately effective by emergency AD 2000-
25-51, issued on December 4, 2000, which contained the requirements of 
this amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before April 3, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-54-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. 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: On December 4, 2000, the Federal Aviation 
Administration (FAA) issued emergency AD 2000-25-51, applicable to 
certain Rolls-Royce Deutschland GmbH (RRD) (formerly BMW Rolls-Royce 
GmbH) BR700-715A1-30, BR700-715B1--30, and BR700-715C1-30 turbofan 
engines. The Luftfahrt-Bundesamt (LBA), which is the airworthiness 
authority for Germany, recently notified the FAA that an unsafe 
condition may exist on certain RRD BR700-715A1-30, BR700-715B1-30, and 
BR700-715C1-30 turbofan engines. The LBA advises that it has received a 
report of a change in the process used to manufacture several HPT stage 
1 and stage 2 disks. That change resulted in a condition that has 
decreased the cyclic life of the disks from the maximum cyclic life 
published in the Time Limits Manual. This condition, if not corrected, 
could result in an uncontained failure of the HPT stage 1 or stage 2 
disk due to exceeded life-cycle limits.
    The LBA has issued AD 2000-358/2 in order to assure the 
airworthiness of these RRD engines in Germany.

Bilateral Airworthiness Agreement

    These engine models are manufactured in Germany, and are 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 LBA has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
LBA, 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.

Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RRD BR700-715A1-30, BR700-715B1-30, and 
BR700-715C1-30 turbofan engines of the same type design, this AD 
requires replacing HPT stage 1 and stage 2 disks, listed by P/N and SN 
in this AD, before exceeding the new reduced life limits.

Immediate Adoption

    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by emergency AD issued on 
December 4, 2000 to all known U.S. owners and operators of RRD BR700-
715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. These 
conditions still exist, and the AD is hereby published in the Federal 
Register as an amendment to Section 39.13 of part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to make it effective to all 
persons.

[[Page 8753]]

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 2000-NE-54-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This 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 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

    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:

2000-25-51  Rolls-Royce Deutschland GmbH: Amendment 39-12098. Docket 
2000-NE-54-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to certain Rolls-Royce Deutschland GmbH (formerly BMW Rolls-Royce 
GmbH) model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 
turbofan engines that are listed by serial number in Table 1 and 
Table 2 of this AD, and that have a high pressure turbine (HPT) 
stage 1 disk, part number (P/N) BRH20009, BRH20010, BRH12167, 
BRH12168, BRH12466, or BRH12467 with a SN that is listed in Table 1; 
or a stage 2 disk, P/N's BRH19349 or BRH19350 with a SN that is 
listed in Table 2. These engines are installed on but not limited to 
McDonnell Douglas Corporation 717 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 an uncontained failure of the HPT stage 1 or stage 2 
disk due to exceeded life-cycle limits, do the following:
    (a) Remove HPT stage 1 disks listed in Table 1 before exceeding 
the cycles-since-new (CSN) in the ``Replace By'' column, and replace 
with serviceable disks.

     Table 1.--HPT Stage 1 Disks By Engine SN, Disk P/N, and Disk SN
------------------------------------------------------------------------
                                                     Disk
        Engine Serial No.             Disk P/N        SN     Replace by
------------------------------------------------------------------------
13111...........................  BRH12466........    312  2600 CSN
13112...........................  BRH12466........    308  2600 CSN
13113...........................  BRH12167........    130  2600 CSN
13118...........................  BRH12467........    330  2600 CSN
13119...........................  BRH12467........    319  2600 CSN
13120...........................  BRH12467........    331  2600 CSN
13139...........................  BRH12168........    154  2600 CSN
13174...........................  BRH20010........    380  2600 CSN
13175...........................  BRH20010........    381  2600 CSN
13176...........................  BRH20010........    378  2600 CSN
13178...........................  BRH20009........    221  2600 CSN
13179...........................  BRH20009........    211  2600 CSN
13180...........................  BRH20009........    228  2600 CSN
13182...........................  BRH20009........    204  2600 CSN
13183...........................  BRH20009........    205  2600 CSN
13184...........................  BRH20009........    230  2600 CSN
13185...........................  BRH20010........    377  2600 CSN
13177...........................  BRH20010........    376  3600 CSN
13181...........................  BRH20009........    199  3600 CSN
13186...........................  BRH20010........    366  3600 CSN
13187...........................  BRH20009........    224  3600 CSN
13192...........................  BRH20009........    202  3600 CSN
13193...........................  BRH20009........    225  3600 CSN
------------------------------------------------------------------------

    (b) Remove HPT stage 2 disks listed in Table 2 before exceeding 
3800 CSN, and replace with serviceable disks.

[[Page 8754]]



     Table 2.--HPT Stage 2 Disks by Engine SN, Disk P/N, and Disk SN
------------------------------------------------------------------------
                                                                    Disk
           Engine Serial No.                     Disk P/N            SN
------------------------------------------------------------------------
13111..................................  BRH19349................    316
13112..................................  BRH19349................    318
13114..................................  BRH19349................    317
13120..................................  BRH19350................    301
13138..................................  BRH19350................    334
------------------------------------------------------------------------

    (c) After effective date of this AD, do not install any HPT 
stage 1 or stage 2 disks except as allowed by paragraphs (a), (b), 
or (d) of this AD.

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 shall submit their requests 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

    (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 aircraft to a location where 
the requirements of this AD can be accomplished.

Effective Date of This AD

    (f) This amendment becomes effective on February 20, 2001, to 
all owners and operators except those to whom it was made 
immediately effective by emergency AD 2000-25-51, issued on December 
4, 2000, which contained the requirements of this amendment.

    Issued in Burlington, Massachusetts on January 24, 2001.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-2609 Filed 2-1-01; 8:45 am]
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