Airworthiness Directives; BMW Rolls-Royce GmbH Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines

[Federal Register Volume 66, Number 50 (Wednesday, March 14, 2001)]
[Rules and Regulations]
[Pages 14826-14828]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-5736]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-48-AD; Amendment 39-12142; AD 2001-05-06]
RIN 2120-AA64


Airworthiness Directives; BMW Rolls-Royce GmbH Models BR700-
710A1-10 and BR700-710A2-20 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 BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 
turbofan engines with fan disk part numbers (P/N's) BRR18803, BRR19248, 
or BRR20791 installed, and BR700-710A2-20 turbofan engines with fan 
disks P/N's BRR19248 or BRR20791 installed. This action requires 
initial and repetitive inspections of these fan disks for cracks, and 
if necessary replacement with serviceable parts. This amendment is 
prompted by reports of cracks in several fan disks in the dovetail 
area. The actions specified in this AD are intended to detect cracks in 
the fan disk, that could result in an uncontained engine failure and 
damage to the airplane.

DATES: Effective March 29, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of March 29, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 14, 2001.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-48-AD, 12 New England Executive Park, 
Burlington, MA

[[Page 14827]]

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.
    The service information referenced in this AD may be obtained from 
Rolls-Royce Deutschland GmbH, Eschenweg 11, D-15827 DAHLEWITZ, Germany, 
telephone: International Access Code 011, Country Code 49, 33 7086-
2935, fax: International Access Code 011, Country Code 49, 33 7086-
3276. 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 Luftfahrt-Bundesamt (LBA), which is the 
airworthiness authority for Germany, recently notified the Federal 
Aviation Administration (FAA) that an unsafe condition may exist on BMW 
RR GmbH models BR700-710A1-10 and BR700-710A2-20 turbofan engines with 
the P/N fan disks listed in this AD. The LBA received several reports 
of cracks in fan disks, in the dovetail area. BMW Rolls-Royce has 
initially determined that these cracks are caused by high-cycle-
fatigue, and that time predictions and cycle predictions for crack 
initiation cannot be accurately determined. BMW RR is investigating the 
cause for fan disk cracking, and may introduce a new part number disk 
as terminating action of the repetitive inspections. This AD may be 
revised when a terminating action is established.

Manufacturer's Service Information

    Rolls-Royce Deutschland (RRD) GmbH has issued Service Bulletin No. 
SB-BR700-72-900229, Revision 2, dated November 23, 2000 that specifies 
procedures for initial and repetitive inspections for fan disk cracks. 
The LBA classified this service bulletin as mandatory and issued 
airworthiness directive (AD) 2000-348, Revision 2, dated November 23, 
2000 in order to ensure the airworthiness of these engines in Germany.

Differences Between Manufacturer's Service Information and This AD

    Although the visual inspection requirements of Service Bulletin No. 
SB-BR700-72-900229, dated November 23, 2000, do not specifically define 
the pass/fail criteria for fan disks, this AD specifically instructs 
the rejection of fan disks that have visual cracks. FAA communication 
with RRD has confirmed that the intent of the service bulletin is to 
require the owner/operator to default to appropriate maintenance 
manuals for pass/fail criteria. A subsequent review of the maintenance 
manuals by the FAA has confirmed that no cracks are allowed in the fan 
disks.

Bilateral Airworthiness Agreement

    This engine model is manufactured in Germany 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 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.

Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design, this AD 
requires initial and repetitive inspections of the fan disks listed in 
this AD for cracks, in accordance with RRD Service Bulletin No. SB-
BR700-72-900229, Revision 2, dated November 23, 2000, and, if 
necessary, replacement with serviceable parts. The inspections must be 
done in accordance with the Service Bulletin described previously in 
this AD.

Immediate Adoption

    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 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 
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-48-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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.

[[Page 14828]]

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 (AD):

2001-05-06  BMW Rolls-Royce GmbH: Amendment 39-12142. Docket 2000-
NE-48-AD.

Applicability

    BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 with fan disks 
part numbers (P/N's) BRR18803, BRR19248, or BRR20791 installed, and 
BR700-710A2-20 turbofan engines with fan disks P/N's BRR19248 or 
BRR20791 installed. These engines are installed on but not limited 
to Bombardier Inc. BD-700-1A10, and Gulfstream Aerospace Corp. G-V 
series 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 (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 detect cracks in the fan disk, that could result in an 
uncontained engine failure and damage to the airplane, accomplish 
the following:

Initial Inspection

    (a) Within 25 flight cycles after the effective date of this AD, 
visually or ultrasonically inspect fan disks in accordance with 
Accomplishment Instructions, Paragraph 3 of Rolls-Royce Deutschland 
(RRD) Service Bulletin No. SB-BR700-72-900229, Revision 2, dated 
November 23, 2000. If any cracks are found, remove disk from service 
and replace with a serviceable disk.

Repetitive Inspections

    (b) Thereafter, in accordance with Accomplishment Instructions, 
Paragraph 3 of Rolls-Royce Deutschland (RRD) Service Bulletin No. 
SB-BR700-72-900229, Revision 2, dated November 23, 2000, inspect 
every 25 flight cycles, using either visual or ultrasonic method, 
except if the initial inspection was a visual inspection, the second 
inspection must be an ultrasonic inspection. Also, perform an 
ultrasonic inspection at intervals not exceeding 450 flight hours 
since the last ultrasonic inspection. If any cracks are found, 
remove disk from service and replace with a serviceable disk.
    (c) For the purposes of this AD, serviceable fan disks are disks 
that have had an initial inspection, either visual or ultrasonic, in 
accordance with Accomplishment Instructions, Paragraph 3 of RRD 
Service Bulletin No. SB-BR700-900229, Revision 2, dated November 23, 
2000, and found not cracked.

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 AD, if any, may be 
obtained from the ECO.

Special Flight Permits

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

Incorporation by Reference

    (f) The inspections required by this AD must be performed in 
accordance with RRD Service Bulletin No. SB-BR700-72-900229, 
Revision 2, dated November 23, 2000. 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 
Rolls-Royce Deutschland GmbH, Eschenweg 11, D-15827 DAHLEWITZ, 
Germany, telephone: International Access Code 011, Country Code 49, 
33 7086-2935, fax: International Access Code 011, Country Code 49, 
33 7086-3276. 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.

Effective Date

    (g) This amendment becomes effective on March 29, 2001.

    Issued in Burlington, Massachusetts, on March 1, 2001.
David A. Downey,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-5736 Filed 3-13-01; 8:45 am]
BILLING CODE 4910-13-U

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