[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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: ``engineprop@faa.gov''. 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:
----------------------------------------------------------------------------------------------------------------
Document No. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
BR700-72-900062............................ 1-8 2 November 3, 1998.
Total pages: 8.
----------------------------------------------------------------------------------------------------------------
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
