[Federal Register Volume 64, Number 223 (Friday, November 19, 1999)]
[Rules and Regulations]
[Pages 63180-63182]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29823]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-74-AD; Amendment 39-11425; AD 98-24-03 R1]
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 revises 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 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 amendment increases 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 
amendment also requires 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. Finally, 
this amendment adds a new paragraph in the compliance section allowing 
the option to incorporate redesigned core engine fairings as the 
terminating action to the required repetitive inspections. This 
amendment is prompted by results of repetitive inspections that 
indicate that the inspection interval can be increased safely, and by 
introduction of redesigned engine core fairings. The

[[Page 63181]]

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 airplane.

DATES: Effective December 27, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before December 27, 1999.
    The incorporation by reference of BRR Service Bulletin BR700-72-
900062, Revision 2, dated November 3, 1998, listed in the regulations 
was approved by the Director of the Federal Register as of March 11, 
1999.
    The incorporation by reference of all other publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 27, 1999.

ADDRESSES: Submit comments 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: ``[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 
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 Federal Aviation Administration 
(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, 7th Floor, suite 700, 
Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by revising Airworthiness 
Directive (AD) 98-24-03, Amendment 39-11050 (64 FR 9056, February 24, 
1999), following a priority letter AD issued November 12, 1998, which 
is applicable to BMW Rolls-Royce GmbH (BRR) Models BR700-710A1-10 and 
BR700-710A2-20 turbofan engines, was published in the Federal Register 
on August 17, 1999 (64 FR 44666). The action proposed to 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 proposed to 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 would be added as an 
alternate to engine core fairing replacement, and an inspection for 
loose engine core fairing(s) would be included to verify correct 
installation on the engine. That action was prompted by results of 
repetitive inspections that indicate that the inspection interval can 
be increased safely. 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.

No Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public.

Optional Terminating Action

    Since publication of the NPRM, BRR has issued Service Bulletin (SB) 
BR700-72-100900, Revision 1, dated September 10, 1999 which introduces 
redesigned engine core fairings thereby allowing the option to 
incorporate this redesigned hardware as the terminating action to the 
required repetitive inspections. The Luftfahrt-Bundesamt (LBA), the 
airworthiness authority for Germany, has reviewed and approved the 
technical contents of this SB.

Difference Between NPRM and Final Rule

    Except for the optional terminating action, there is no change 
between the proposal and this final rule.

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.

Economic Analysis

    There exists no adverse economic impact because this revised rule 
only increases the repetitive inspection interval. However, if an 
operator chooses to install the new engine core fairings, the labor is 
approximately 25 work hours at the average labor rate of $60 per work 
hour. Required parts are approximately $141,372. The total cost per 
engine of the new engine core fairings is $142,872. The manufacturer 
has advised the FAA that they may lower the economic burden on 
operators by reimbursing the costs associated with the incorporation of 
the redesigned engine core fairings.

Adoption of the Rule

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the changes described previously.

Comments Invited

    Since the optional terminating action involving installation of new 
engine core fairings was not in the NPRM, comments are invited from the 
public on this option and its economic impact. 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 98-ANE-74-AD.'' The

[[Page 63182]]

postcard will be date stamped and returned to the commenter.

Regulatory Impact

    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.
    For the reasons discussed above, I certify that this action (1) Is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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

    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, 
Amendment 39-11425, to read as follows:

98-24-03 R1 BMW Rolls-Royce GmbH: Amendment 39-11425. Docket 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 (f) 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:

Inspections, Repair, Replacement, and Torquing

    (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.

Optional Terminating Action

    (e) Incorporation of the redesigned engine core fairings in 
accordance with BRR SB BR700-72-100900, Revision 1, dated September 
10, 1999, constitutes terminating action for the requirements 
specified in paragraphs (a), (b), (c), and (d) of this AD.

Alternative Methods of Compliance

    (f) 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.

Incorporation by Reference

    (g) The actions required by this AD shall be done in accordance 
with the following BRR SBs: BR700-72-900062, Revision 1, dated 
October 29, 1998; Revision 2, dated November 3, 1998; Revision 3, 
dated March 24, 1999; and BR700-72-100900, Revision 1, dated 
September 10, 1999. 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.
    (h) This amendment becomes effective on December 27, 1999.

    Issued in Burlington, Massachusetts, on November 5, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-29823 Filed 11-18-99; 8:45 am]
BILLING CODE 4910-13-U