[Federal Register Volume 64, Number 36 (Wednesday, February 24, 1999)]
[Rules and Regulations]
[Pages 9056-9058]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-4368]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-74-AD; Amendment 39-11050; AD 98-24-03]
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 document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 98-24-03 that was sent previously 
to all known U.S. owners and operators of BMW Rolls-Royce GmbH (BRR) 
Models BR700-710A1-10 and BR700-710A2-20 turbofan engines by individual 
letters. This AD requires repetitive visual inspections of the fairing 
and fasteners for correct installation and damage, and verification 
that the engine core fairing fasteners are torqued to the higher torque 
value. This amendment is prompted by a report of an engine compressor 
core fairing failure during engine ground runs. The actions specified 
by this AD are intended to prevent engine compressor or combustion core 
fairing detachment and damage to the engine bypass duct, resulting in 
engine failure and damage to the aircraft.

DATES: Effective March 11, 1999, to all persons except those persons to 
whom it was made immediately effective by priority letter AD 98-24-03, 
issued on November 12, 1998, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 11, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before April 26, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 98-ANE-74-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 applicable service information may be obtained from BMW Rolls-
Royce GmbH, Eschenweg 11, D-15827 Dahlewitz, Germany; telephone 011-49-
33-7086-1883; fax 011-49-33-7086-3276. 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: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On November 12, 1998, the Federal Aviation 
Administration (FAA) issued priority letter airworthiness directive 
(AD) 98-24-03, applicable to BMW Rolls-Royce GmbH (BRR) Models BR700-
710A1-10 and BR700-710A2-20 turbofan engines, which requires visual 
inspections of the fairing and fasteners to ensure proper installation 
and for cracks or damage, and if cracked or damaged, replacement with 
serviceable parts, and also requires that the engine core fairing 
fasteners be torqued to a higher torque value. That action was prompted 
by a report of an engine compressor core fairing failure during engine 
ground runs on a BRR Model BR700-710A1-10 turbofan engine installed on 
a Gulfstream G-V model aircraft. Preliminary investigation indicates 
that the upper right compressor core fairing became detached and lodged 
in the engine bypass duct. The engine bypass duct was substantially 
damaged, resulting in engine removal. Following the event, additional 
in-field engine inspections of the compressor and combustion core 
fairings found some engine core fairing fasteners that were cracked, 
loose, not engaged, or no longer engageable.
    The FAA received a comment to the Priority Letter AD recommending 
that

[[Page 9057]]

the language of Paragraph (a) in the compliance section be changed to 
clarify the intent. The commenter expressed concern that Paragraph (a) 
may be interpreted as requiring the removal and disassembly of the 
fairing and fasteners in order to visually inspect for cracks. The FAA 
disagrees. The language in Paragraph (a) is adequate without adding 
clarification. The intent of this paragraph not to remove or 
disassemble the fairings or fasteners but to visually inspect the 
fairings and fasteners for correct installation. Any damage or cracked 
hardware found during this visual inspection should be replaced.
    Although the investigation continues, the FAA has determined that 
if this event occurred during flight, the damaged bypass duct could be 
potentially hazardous to the aircraft. This condition, if not 
corrected, could result in engine compressor or combustion core fairing 
detachment and damage to the engine bypass duct, resulting in engine 
failure and damage to the aircraft.
    The FAA has reviewed and approved the technical contents of BRR 
Service Bulletin (SB) BR700-72-900062, Revision 2, dated November 3, 
1998, that describes visual inspections to ensure proper installation 
of the engine compressor and combustion core fairings (also referred to 
as the engine core fairing) and increases the torque limits for the 
fairing fasteners.
    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, the FAA issued priority 
letter AD 98-24-03 to prevent engine failure and damage to the 
aircraft. The AD requires, prior to further flight, and thereafter at 
50 hours time in service (TIS) intervals, visual inspection of the 
fairing and fasteners for correct installation and for cracks and 
damage, and verification that the engine core fairing fasteners are 
torqued to the higher torque value. These actions are required to be 
accomplished in accordance with the SB described previously.
    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 individual letters 
issued on November 12, 1998, to all known U.S. owners and operators of 
BRR Models BR700-710A1-10 and BR700-710A2-20 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.

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 98-ANE-74-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:

98-24-03  BMW Rolls-Royce GmbH: Amendment 39-11050. Docket 98-ANE-
74-AD.

    Applicability: BMW Rolls-Royce GmbH (BRR) Model BR700-710A1-10 
and BR700-710A2-20 turbofan engines installed on, but not limited 
to, Gulfstream Aerospace G-V and Bombardier BD-700-1A10 model 
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 (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: Required as indicated, unless accomplished 
previously.
    To prevent engine compressor and combustion core fairing 
detachment which could result in damage to the engine bypass duct, 
engine failure and damage to the aircraft, accomplish the following:
    (a) Prior to further flight, visually inspect the engine 
compressor and combustion core

[[Page 9058]]

fairings and fasteners to ensure correct installation and for cracks 
or damage, and if cracked or damaged, replace with serviceable 
parts. Torque all the fasteners to the increased torque value, in 
accordance with BRR Service Bulletin (SB) BR700-72-900062, Revision 
1, dated October 29, 1998, or Revision 2, dated November 3, 1998.
    (b) Thereafter, at intervals not to exceed 50 hours time in 
service (TIS) since last inspection, visually inspect the engine 
compressor and combustion core fairings and fasteners to ensure 
correct installation and for cracks or damage and, if cracked or 
damaged, replace with serviceable parts. Torque all the fasteners to 
the increased torque value, in accordance with BRR SB BR700-72-
900062, Revision 2, dated November 3, 1998.
    (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. 
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.

    (d) The actions required by this AD shall be done in accordance 
with the following BRR SB:

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                Document No.                    Pages       Revision                      Date
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BR700-72-900062............................          1-8            2  November 3, 1998.
    Total pages: 8.
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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 BMW Rolls-Royce GmbH, Eschenweg 
11, D-15827 Dahlewitz, Germany; telephone 011-49-33-7086-1883; fax 
011-49-33-7086-3276. 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.
    (e) This amendment becomes effective March 11, 1999, to all 
persons except those persons to whom it was made immediately 
effective by priority letter AD 98-24-03, issued November 12, 1998, 
which contained the requirements of this amendment.

    Issued in Burlington, Massachusetts, on February 16, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-4368 Filed 2-23-99; 8:45 am]
BILLING CODE 4910-13-P