AD 2001-01-01

[Federal Register Volume 66, Number 10 (Tuesday, January 16, 2001)]
[Rules and Regulations]
[Pages 3448-3450]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-917]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-44-AD; Amendment 39-12071; AD 2001-01-01]
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

[[Page 3449]]

applicable to BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 and 
BR700-710A2-20 turbofan engines with oil filter differential pressure 
switch part number (P/N) 21SN04-419 or P/N 21SN04-431 installed. This 
action requires inspections of oil filter differential pressure 
switches, and replacement if necessary, in accordance with Rolls-Royce 
Service Bulletin No. SB-BR700-79-900215, Revision 2, dated August 2, 
2000. This amendment is prompted by a report of severe engine oil loss, 
caused by oil leakage from a defective oil filter differential pressure 
switch. The actions specified in this AD are intended to prevent 
defective oil filter differential pressure switches from causing severe 
engine oil loss, resulting in in-flight shutdowns.

DATES: Effective January 31, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of January 31, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before March 19, 2001.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-44-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#a1988cc0cfc48cc0c5c2ceccccc4cfd5e1c7c0c08fc6ced7"><span class="__cf_email__" data-cfemail="7d44501c1318501c191e1210101813093d1b1c1c531a120b">[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 
BMW Rolls-Royce GmbH, Postfach 1246, 61402 Oberursel, 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. The 
LBA received a report of severe engine oil loss, caused by oil leaking 
from a defective oil filter differential pressure switch, resulting in 
an in-flight engine shutdown. BMW RR has identified and provided in a 
list, serial numbers for pressure switches that are not defective. BMW 
RR has determined that for pressure switches with less than 200 flight 
hours-since-new, that are not one of the listed switches, and are not 
leaking, 50 flight hours will be allowed after the effective date of 
this AD before the required replacement with a serviceable switch. For 
pressure switches with 200 or more flight hours-since-new, 150 flight 
hours will be allowed after the effective date of this AD before the 
required replacement with a serviceable switch. This is based on 
calculations that pressure switches with 200 or more flight hours-
since-new have successfully passed a threshold for failure. An analysis 
conducted by BMW RR revealed that the engine shutdown rate due to oil 
leaking from defective oil filter differential pressure switches is 
unacceptable, and could result in multiple engine in-flight shutdowns. 
The actions specified in this AD are intended to prevent defective oil 
filter differential pressure switches from causing severe engine oil 
loss, resulting in in-flight engine shutdowns.

Service Information

    RR has issued Service Bulletin No. SB-BR700-79-900215, Revision 2, 
dated August 2, 2000, which specifies procedures for inspecting, 
marking, and if necessary replacing oil filter differential pressure 
switch P/N 21SN04-419 or P/N 21SN04-431 with a serviceable switch. The 
LBA issued AD No. 2000-257/2, in response to the service bulletin to 
assure the airworthiness of these 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 
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 registered in 
the United States, this AD is being issued to prevent defective oil 
filter differential pressure switch P/N 21SN04-419 or P/N 21SN04-431 
from causing severe engine oil loss, resulting in in-flight shutdown. 
The actions would be required to be accomplished in accordance with the 
service bulletin described previously.

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 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 
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. 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-44-AD.'' The postcard will be date stamped and 
returned to the commenter.

[[Page 3450]]

Regulatory Impact

    This action 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 
responsibilities among the various levels of government. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this proposal.
    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:

2001-01-01  BMW Rolls-Royce GmbH: Amendment 39-12071. Docket 2000-
NE-44-AD.

    Applicability: This airworthiness directive (AD) applies to BMW 
Rolls-Royce (RR) GmbH models BR700-710A1-10 and BR700-710A2-20 
turbofan engines with oil filter differential  pressure  switch  
part  number (P/N) 21SN04-419 or P/N 21SN04-431 installed. These 
engines are installed on, but not limited to Bombardier Inc. BD-700 
and Gulfstream Aerospace Corp. G-V series 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 (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

    Compliance with this AD is required as indicated, unless already 
done. To prevent defective oil filter differential pressure switches 
from causing severe engine oil loss, resulting in in-flight 
shutdowns, perform the following:

Number Checking, Marking, and Replacement

    (a) Within 50 flight hours after the effective date of this AD, 
mark or replace the oil filter differential pressure switch as 
follows:
    (1) If the oil filter differential pressure switch serial number 
is listed in Appendix 1 of RR Service Bulletin SB-BR700-79-900215, 
Revision 2, dated August 2, 2000, then mark the switch in accordance 
with the Accomplishment Instructions, Section 3, of RR Service 
Bulletin SB-BR700-79-900215, Revision 2, dated August 2, 2000. No 
further action is required.
    (2) If the oil filter differential pressure switch serial number 
is not listed in Appendix 1 of RR Service Bulletin SB-BR700-79-
900215, Revision 2, dated August 2, 2000, then replace the switch as 
follows:
    (i) For oil pressure switches with less than 200 flight hours-
since-new on the effective date of this AD, replace the pressure 
switch with a serviceable switch, within 50 flight hours after the 
effective date of this AD, in accordance with Accomplishment 
Instructions, Section 3, Part 2 of RR Service Bulletin SB-BR700-79-
900215, Revision 2, dated August 2, 2000.
    (ii) For oil pressure switches with 200 or more flight hours-
since-new on the effective date of this AD, replace the pressure 
switch with a serviceable switch, within 150 flight hours after the 
effective date of this AD, in accordance with Accomplishment 
Instructions, Section 3, Part 2 of RR Service Bulletin SB-BR700-79-
900215, Revision 2, dated August 2, 2000.

Definition of Serviceable Switch

    (b) For the purpose of this AD, the definition of a serviceable 
switch is an oil filter differential pressure switch P/N 21SN04-419 
or 21SN04-431 that has a manufacturer-applied orange stripe on the 
switch cap, or, a pressure switch whose serial number is listed in 
Appendix 1 of RR Service Bulletin SB-BR700-79-900215, Revision 2, 
dated August 2, 2000, and has been marked with orange paint in 
accordance with the Accomplishment Instructions, Section 3, of RR 
Service Bulletin SB-BR700-79-900215, Revision 2, dated August 2, 
2000.

Alternative Methods of Compliance

    (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 (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

    (d) 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

    (e) The actions required by this AD must be performed in 
accordance with BMW RR Service Bulletin No. SB-BR700-79-900215, 
Revision 2, dated August 2, 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 from 
BMW Rolls-Royce GmbH, Postfach 1246, 61402 Oberursel, 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 of This AD

    (f) This amendment becomes effective on January 31, 2001.

    Issued in Burlington, Massachusetts, on January 4, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-917 Filed 1-12-01; 8:45 am]
BILLING CODE 4910-13-P