Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines

[Federal Register Volume 68, Number 70 (Friday, April 11, 2003)]
[Rules and Regulations]
[Pages 17727-17729]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-8327]



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Federal Register / Vol. 68, No. 70 / Friday, April 11, 2003 / Rules 
and Regulations

[[Page 17727]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-48-AD; Amendment 39-13107; AD 2003-07-11]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
(formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) 
models BR700-710A1-10 turbofan engines with fan disc part numbers (P/
Ns) BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 
turbofan engines with fan discs P/Ns BRR19248 or BRR20791 installed. 
That AD currently requires initial and repetitive inspections of these 
fan discs for cracks, and if necessary replacement with serviceable 
parts. This amendment requires the same inspections but with longer 
intervals between repetitive inspections under certain conditions, and 
requires removal of any dry film lubricant coating from the front face 
of the fan disc for visual inspections. This amendment is prompted by 
reevaluation by RRD of results from a fleet-wide inspection campaign, 
reevaluation of existing repetitive inspection interval requirements, 
and by a revised service bulletin (SB) that introduces improved 
inspection procedures. The actions specified by this AD are intended to 
detect cracks in the fan disc, that could result in an uncontained 
engine failure and damage to the airplane.

DATES: Effective April 28, 2003. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of April 28, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before June 10, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-48-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. 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 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 DAHLEWITZ, 
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, by appointment, 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: On March 1, 2001, the FAA issued AD 2001-05-
06, Amendment 39-12142 (66 FR 14826, March 14, 2001), to require 
initial and repetitive inspections of fan discs for cracks, and if 
necessary replacement with serviceable parts. The Luftfahrt-Bundesamt 
(LBA), which is the airworthiness authority for Germany, notified the 
FAA that an unsafe condition may exist on Rolls-Royce Deutschland Ltd & 
Co KG models BR700-710A1-10 turbofan engines with fan disc P/Ns 
BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan 
engines with fan discs P/Ns BRR19248 or BRR20791 installed. The LBA 
received several reports of cracks in fan discs, in the dovetail area. 
RRD determined that these cracks were caused by high-cycle fatigue, and 
that time predictions and cycle predictions for crack initiation could 
not be accurately determined. Investigation by RRD has been ongoing. 
That condition, if not corrected, could result in an uncontained engine 
failure and damage to the airplane.
    Since that AD was issued, RRD has reevaluated results from a fleet-
wide inspection campaign, has reevaluated the existing repetitive 
inspection interval requirements, and has issued SB No. SB-BR700-72-
900229, Revision 5, dated January 8, 2003.

Manufacturer's Service Information

    RRD has issued SB No. SB-BR700-72-900229, Revision 5, dated January 
8, 2003, that specifies procedures for removing any dry film lubricant 
coating from the front face of the fan disc to improve visual 
inspections, and initial and repetitive inspections for cracks in fan 
discs. The LBA classified this service bulletin as mandatory and issued 
AD 2000-348, Revision 5, dated March 6, 2003, in order to ensure the 
airworthiness of these RRD models BR700-710A1-10 turbofan engines and 
BR700-710A2-20 turbofan engines in Germany.

Differences Between This AD and the Manufacturer's Service Information

    Although the visual inspection requirements of RRD SB No. SB-BR700-
72-900229, Revision 5, dated January 8, 2003, do not specifically 
define the pass or fail criteria for fan discs, this AD specifically 
instructs the rejection of fan discs that have visual cracks. FAA 
communication with RRD has confirmed that the intent of the service 
bulletin is to require the owner or operator to default to appropriate 
maintenance manuals for pass or fail criteria. A subsequent review of 
the maintenance manuals by the FAA has confirmed that no cracks are 
allowed in the fan discs.

Bilateral Airworthiness Agreement

    This engine model is manufactured in Germany and is type 
certificated for

[[Page 17728]]

operation in the United States under the provisions of Sec.  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.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other RRD models BR700-710A1-10 turbofan engines 
and BR700-710A2-20 turbofan engines of the same type design, this AD 
requires for fan discs listed in this AD, removal of any dry film 
lubricant coating from the fan disc front face to improve visual 
inspections and initial and repetitive inspections for cracks. The 
actions must be done in accordance with the service bulletin described 
previously.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Immediate Adoption of This AD

    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 
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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-48-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule 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 and 
responsibilities among the various levels of government. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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

0
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

0
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]

0
2. Section 39.13 is amended by removing Amendment 39-12142 (66 FR 
14826, March 14, 2001) and by adding a new airworthiness directive, 
Amendment 39-13107, to read as follows:

2003-07-11 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-13107. 
Docket No. 2000-NE-48-AD. Supersedes AD 2001-05-06, Amendment 39-
12142.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH) models BR700-710A1-
10 turbofan engines with fan disc part numbers (P/Ns) BRR18803, 
BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan engines 
with fan discs P/Ns BRR19248 or BRR20791 installed. These engines 
are installed on, but not limited to Bombardier Inc. BD-700-1A10, 
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 (h) 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 detect cracks in the fan disc that could result in an 
uncontained engine failure and damage to the airplane, do the 
following:

Initial Inspection

Engines With Fan Discs P/Ns BRR18803 and BRR19248 Installed

    (a) For BR700-710A1-10 engines with fan discs, P/Ns BRR18803 and 
BRR19248 installed, and BR700-710A2-20 engines with fan discs, P/N 
BRR19248 installed, do the following:
    (1) If the last fan disc inspection was a visual inspection 
performed using RRD SB No. SB-BR700-900229, Revision 3, dated July 
12, 2001, Revision 4, dated December 20, 2001, or Revision 5, dated 
January 8, 2003, visually or ultrasonically inspect fan disc within 
25 flight cycles-since-last inspection (CSLI), in accordance with 
paragraphs A through F of the applicable Part 1 or Part 2 of the 
Accomplishment Instructions of RRD SB No. SB-BR700-900229, Revision 
5, dated January 8, 2003.

[[Page 17729]]

    (2) If the last fan disc inspection was an ultrasonic inspection 
performed using RRD SB No. SB-BR700-900229, Revision 3, dated July 
12, 2001, Revision 4, dated December 20, 2001, or Revision 5, dated 
January 8, 2003, visually or ultrasonically inspect fan disc within 
75 CSLI, in accordance with paragraphs A through F of the applicable 
Part 1 or Part 2 of the Accomplishment Instructions of RRD SB No. 
SB-BR700-900229, Revision 5, dated January 8, 2003.
    (3) For engines that have not yet been inspected, visually or 
ultrasonically inspect fan disc within 25 flight cycles after the 
effective date of this AD, in accordance with paragraphs A through F 
of the applicable Part 1 or Part 2 of the Accomplishment 
Instructions of RRD SB No. SB-BR700-900229, Revision 5, dated 
January 8, 2003.
    (4) If any cracks are found, remove disc from service and 
replace with a serviceable disc.

Engines With Fan Discs P/N BRR20791 Installed

    (b) For BR700-710A1-10 engines with serial numbers (SNs) 11452 
and lower, and BR700-710A2-20 engines with SNs 12352 and lower, with 
fan discs P/N BRR20791 installed, do the following:
    (1) If the last fan disc inspection was a visual inspection 
performed using RRD SB No. SB-BR700-900229, Revision 3, dated July 
12, 2001, Revision 4, dated December 20, 2001, or Revision 5, dated 
January 8, 2003, visually or ultrasonically inspect fan disc within 
25 CSLI, in accordance with paragraphs A through F of the applicable 
Part 1 or Part 2 of the Accomplishment Instructions of RRD SB No. 
SB-BR700-900229, Revision 5, dated January 8, 2003.
    (2) If the last fan disc inspection was an ultrasonic inspection 
performed using RRD SB No. SB-BR700-900229, Revision 3, dated July 
12, 2001, Revision 4, dated December 20, 2001, or Revision 5, dated 
January 8, 2003, visually or ultrasonically inspect fan disc within 
150 CSLI, in accordance with paragraphs A through F of the 
applicable Part 1 or Part 2 of the Accomplishment Instructions of 
RRD SB No. SB-BR700-900229, Revision 5, dated January 8, 2003.
    (3) For engines that have not yet been inspected, visually or 
ultrasonically inspect fan disc within 25 flight cycles after the 
effective date of this AD, in accordance with paragraphs A through F 
of the applicable Part 1 or Part 2 of the Accomplishment 
Instructions of RRD SB No. SB-BR700-900229, Revision 5, dated 
January 8, 2003.
    (4) If any cracks are found, remove disc from service and 
replace with a serviceable disc.
    (c) For BR700-710A1-10 engines with SNs 11453 and higher, and 
BR700-710A2-20 engines with SNs 12353 and higher with fan discs P/N 
BRR20791 installed, do the following:
    (1) Visually or ultrasonically inspect fan discs within 150 
flight cycles-since-new (CSN), in accordance with paragraphs A 
through F of the applicable Part 1 or Part 2 of the Accomplishment 
Instructions of RRD SB No. SB-BR700-900229, Revision 5, dated 
January 8, 2003.
    (2) For engines that have not yet been inspected, visually or 
ultrasonically inspect fan disc within 25 flight cycles after the 
effective date of this AD, in accordance with paragraphs A through F 
of the applicable Part 1 or Part 2 of the Accomplishment 
Instructions of RRD SB No. SB-BR700-900229, Revision 5, dated 
January 8, 2003.
    (3) If any cracks are found, remove disc from service and 
replace with a serviceable disc.

Repetitive Inspections

    (d) Except for engines listed in paragraph (e) of this AD, 
perform repetitive inspections using the criteria in paragraphs (a) 
through (b)(4), and (f) of this AD.
    (e) For BR700-710A1-10 engines with SNs 11453 and higher, and 
BR700-710A2-20 engines with SNs 12353 and higher with fan discs P/N 
BRR20791 installed, perform repetitive inspections using the 
criteria in paragraphs (c) through (c)(3), and (f) of this AD.
    (f) For all discs, perform a visual and ultrasonic inspection 
before accumulating 500 CSN, in accordance with paragraphs A through 
F of the applicable Part 1 or Part 2 of the Accomplishment 
Instructions of RRD SB No. SB-BR700-900229, Revision 5, dated 
January 8, 2003.
    (g) Thereafter, for all discs, perform a visual and an 
ultrasonic inspection before accumulating 500 cycles-since-the last 
visual and ultrasonic inspections.

Inspection Reporting Requirements

    (g) Report defects in accordance with the applicable Part 1 or 
Part 2 of RRD SB No. SB-BR700-900229, Revision 5, dated January 8, 
2003. Reporting requirements have been approved by the Office of 
Management and Budget (OMB) and assigned OMB control number 2120-
0056.

Alternative Methods of Compliance

    (h) 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 must submit their request 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 airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (i) Special flight permits may be issued in accordance with 
Sec. Sec.  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 done.

Documents That Have Been Incorporated by Reference

    (j) The inspection must be done in accordance with Rolls-Royce 
Deutschland Ltd & Co KG Service Bulletin No. SB-BR700-72-900229, 
Revision 5, dated January 8, 2003. 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 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 
DAHLEWITZ, 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.

    Note 3: The subject of this AD is addressed in LBA AD 2000-348, 
Revision 5, dated March 6, 2003.

Effective Date

    (k) This amendment becomes effective on April 28, 2003.

    Issued in Burlington, Massachusetts, on April 1, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-8327 Filed 4-10-03; 8:45 am]
BILLING CODE 4910-13-P

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