[Federal Register Volume 64, Number 158 (Tuesday, August 17, 1999)]
[Proposed Rules]
[Pages 44666-44667]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21332]
[[Page 44666]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-74-AD]
Airworthiness Directives; BMW Rolls-Royce GmbH Models BR700-
710A1-10 and BR700-710A2-20 Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise an existing airworthiness
directive (AD) applicable to BMW Rolls-Royce GmbH (BRR) Models BR700-
710A1-10 and BR700-710A2-20 turbofan engines. The existing AD currently
requires initial and repetitive visual inspections of the engine
compressor and combustion core fairings (also referred to as the engine
core fairings) and fasteners for correct installation and damage, and
verification that the engine core fairing fasteners are torqued to a
higher torque value. This action would increase the repetitive
inspection interval to 150 hours time-in-service (TIS) following an
initial inspection and follow-on inspection at the current 50 hours TIS
interval. This action also would require an initial inspection and
follow-on inspection at a 50 hours TIS interval following any engine
core fairing or fastener removal, repair, or replacement. Repair of
engine core fairings has been added as an alternate to engine core
fairing replacement, and an inspection for loose engine core fairing(s)
has been included to verify correct installation on the engine. This
proposal is prompted by results of repetitive inspections that indicate
that the inspection interval can be increased safely. The actions
specified by the proposed 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 airplane.
DATES: Comments must be received by September 16, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
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-ane-
[email protected]''. Comments sent via the Internet must contain the
docket number in the subject line. Comments may be inspected at this
location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule 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.
FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7744, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal 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.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-ANE-74-AD, 12 New England Executive
Park, Burlington, MA 01803-5299.
Discussion
On February 16, 1999, the Federal Aviation Administration (FAA)
issued airworthiness directive (AD) 98-24-03, Amendment 39-11050 (64 FR
9056, February 24, 1999), following a priority letter AD issued
November 12, 1998, applicable to BMW Rolls-Royce GmbH (BRR) Models
BR700-710A1-10 and BR700-710A2-20 turbofan engines. That AD requires
initial and repetitive visual inspections of the engine compressor and
combustion core fairings (also referred to as the engine core fairings)
and fasteners for correct installation and damage, and verification
that the engine core fairing fasteners are torqued to the 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 aircraft. That
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 airplane.
Since the issuance of that AD, the Luftfahrt-Bundesamt (LBA), which
is the airworthiness authority for Germany, has notified the FAA that
they have determined, based on ongoing investigations and results of
successful repetitive inspections, that the inspection interval can be
safely increased. They also determined that if an engine core fairing
was removed, an initial inspection and follow-on inspection at the
current 50 hour TIS interval would be required to insure correct
installation, before the 150 hour repetitive time-in-service (TIS)
interval is permitted. They also instituted an inspection requirement
for loose engine core fairings to verify proper installation and
allowed the use of repaired engine core fairings. The LBA issued AD
1998-467/2 following publication of BRR Service Bulletin (SB) No.
BR700-72-900062, Revision 3, dated March 24,1999, that increases the
repetitive inspection intervals.
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
[[Page 44667]]
determined that AD action is necessary for products of this type design
that are certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would revise AD 98-24-03 to increase the repetitive
inspection interval to 150 hours time-in-service (TIS) following a
successful initial inspection and one follow-on inspection at the
current 50 hours TIS inspection interval. Any engine core fairings or
fasteners that have been removed, repaired, or replaced will require an
initial inspection before flight and one follow-on inspection at the 50
hours TIS interval before the 150 hour TIS inspection interval is
allowed.
There exists no adverse economic impact because this proposed rule
only increases the repetitive inspection interval.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities under
the criteria of the Regulatory Flexibility Act. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 removing Amendment 39-11050 (64 FR
9056, February 24, 1999), and by adding a new airworthiness directive,
to read as follows:
BMW Rolls-Royce GmbH: Docket No. 98-ANE-74-AD. Revises AD 98-24-03,
Amendment 39-11050.
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 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 (e) 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 (also
referred to as the engine 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 core
fairings and fasteners to ensure correct installation and for
cracks, loose fairings, or fasteners, and if loose, cracked,
damaged, or improperly installed, repair or 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, or
Revision 3, dated March 24, 1999.
(b) Thereafter, except as provided in paragraphs (c) or (d) of
this AD, at intervals not to exceed 50 hours time-in-service (TIS)
since last inspection, visually inspect the engine core fairings and
fasteners for cracks, loose fairings, or fasteners, and, if loose,
cracked, or damaged, repair or 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, or Revision 3, dated March 24, 1999.
(c) Following an initial inspection in accordance with paragraph
(a) of this AD, and one follow-on inspection in accordance with
paragraph (b), if both inspections found no cracks, damage, loose
fairings or fasteners the repetitive inspection interval may be
increased to 150 hours TIS since last inspection in accordance with
the procedures described in paragraph (b) of this AD.
(d) Reinspection and retorquing prior to further flight is
required in accordance with paragraph (a) of this AD, following any
engine core fairing or fastener which has been removed, repaired or
replaced. One successful follow-on inspection and retorque in
accordance with paragraph (b) of this AD must be accomplished before
the repetitive 150 hour TIS inspection interval described in
paragraph (c) of this AD is permitted.
(e) 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.
Issued in Burlington, Massachusetts, on August 11, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-21332 Filed 8-16-99; 8:45 am]
BILLING CODE 4910-13-U