Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines, 38627-38630 [05-13135]
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Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Proposed Rules
Hamilton Sundstrand: Docket No. FAA–
2005–21719; Directorate Identifier 2005–
NE–19–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
September 6, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Hamilton
Sundstrand Power Systems (formerly
Sundstrand Power Systems) auxiliary power
units (APUs) models T–62T–46C2, T–62T–
46C2A, T–62T–46C3, T–62T–46C7, and T–
62T–46C7A, with compressor impeller
assembly, part number (P/N) 4502020 or
4502020A installed. These APUs are
installed on, but not limited to, BAE Systems
AVRO 146, Fokker 50, Saab 2000, and Saab
340 airplanes.
Unsafe Condition
(d) This AD results from two reports of
uncontained failures of compressor impeller
assemblies. We are issuing this AD to prevent
an uncontained APU failure and damage to
the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
(f) For APUs with compressor impeller
assemblies that have 12,000 or more cyclessince-new (CSN) accumulated on the
effective date of this AD, remove compressor
impeller assemblies from service before
accumulating 500 additional cycles.
(g) For APUs with compressor impeller
assemblies that have fewer than 12,000 CSN
on the effective date of this AD, remove
compressor impeller assemblies from service
at or before accumulating 12,500 CSN.
Alternative Methods of Compliance
(h) The Manager, Los Angeles Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Related Information
(i) Hamilton Sundstrand Service Bulletins
No. 4500090–49–33, dated January 6, 2005,
No. 4500482–49–33, dated January 6, 2005,
No. 4501578–49–22, dated January 13, 2005,
No. 4501690–49–47, dated November 19,
2004, and No. 4501909–49–16, dated January
13, 2005, pertain to the subject of this AD.
Issued in Burlington, Massachusetts, on
June 28, 2005.
Diane S. Romanosky,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–13134 Filed 7–1–05; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000–NE–48–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (Formerly
Rolls-Royce Deutschland GmbH,
formerly BMW Rolls-Royce GmbH)
Models BR700–710A1–10 and BR700–
710A2–20 Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce
Deutschland Ltd & Co KG (RRD)
(formerly Rolls-Royce Deutschland
GmbH, formerly BMW Rolls-Royce
GmbH) models BR700–710A1–10 and
BR700–710A2–20 turbofan engines.
That AD currently requires initial and
repetitive visual and ultrasonic
inspections of fan discs, part numbers
(P/Ns) BRR18803, BRR19248, and
BRR20791 for cracks, and if necessary,
replacement with serviceable parts. This
proposed AD would require the same
inspections of these fan discs, with
certain old design P/N fan blades
installed. This proposed AD would
extend the inspection interval for
certain fan discs having new design P/
N fan blades installed. Also, this
proposed AD would add as optional
terminating action to the repetitive
inspections, installation of certain P/N
new fan discs, certain P/N new fan
blades, and engine fan speed (N1) Keep
Out Zone software. This proposed AD
results from a revised RRD service
bulletin (SB) that introduces relaxed
inspection intervals for certain P/N
combinations of fan discs and fan
blades, and introduces improved design
fan discs and fan blades. We are
proposing this AD to detect and prevent
cracks in the fan disc that could result
in an uncontained engine failure and
damage to the airplane.
DATES: We must receive any comments
on this proposed AD by September 6,
2005.
Use one of the following
addresses to submit comments on this
proposed AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2000–NE–
ADDRESSES:
PO 00000
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38627
48–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
You can get the service information
identified in this proposed AD from
Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, 15827 BlankenfeldeMahlow, Germany, telephone:
International Access Code 011, Country
Code 49, (0) 33–7086–1768, fax:
International Access Code 011, Country
Code 49, (0) 33–7086–3356.
You may examine the AD docket, by
appointment, at the FAA, New England
Region, Office of the Regional Counsel,
12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; telephone: (781) 238–7747, fax:
(781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
2000–NE–48–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On April 1, 2003, the FAA issued AD
2003–07–11, Amendment 39–13107 (68
FR 17727, April 11, 2003). That AD
requires initial and repetitive visual and
ultrasonic inspections of fan discs, P/Ns
BRR18803, BRR19248, and BRR20791,
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for cracks, and if necessary, replacement
with serviceable parts.
FAA’s Determination and Requirements
of the Proposed AD
products identified in this rulemaking
action.
Actions Since AD 2003–07–11 Was
Issued
Since AD 2003–07–11 was issued,
RRD has reevaluated the existing
repetitive inspection interval
requirements, and has introduced new
design fan discs and fan blades.
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. Therefore, we are
proposing this AD, which would
require:
• For fan disc P/N BRR18803,
BRR19248, BRR20791, BRR24829,
BRR24829, or FW33929 installed, initial
and repetitive inspections for cracks.
• As optional terminating action to
the repetitive inspection requirements
of the proposed AD, installation of a
new fan disc P/N FW33927, new fan
blades P/N FW33513 or P/N FW33980,
and N1 Keep Out Zone software.
The proposed AD would require that
you do the inspections using the service
information described previously.
Regulatory Findings
Relevant Service Information
We have reviewed and approved the
technical contents of RRD SB No. SB–
BR700–72–900229, Revision 6, dated
February 23, 2005, that describes
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. That
SB also introduces the installation of a
new design fan disc and new design fan
blades. The Luftfahrt-Bundesamt (LBA),
which is the aviation authority for
Germany, classified this service bulletin
as mandatory and issued AD 2000–348,
Revision 6, dated March 31, 2005, 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 the Proposed AD
and the Service Information
Although the visual inspection
requirements of RRD SB No. SB–BR700–
72–900229, Revision 6, dated February
23, 2005, do not specifically define the
pass or fail criteria for fan discs, this
proposed AD would specifically instruct
the rejection of fan discs that have
visual cracks. We communicated with
RRD and 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. We subsequently
reviewed the maintenance manuals and
confirmed that no cracks are allowed in
the fan discs.
Bilateral Agreement Information
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. In keeping
with this bilateral airworthiness
agreement, the LBA has kept the FAA
informed of the situation described
above. We have 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.
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Costs of Compliance
There are about 500 RRD models
BR700–710A1–10 and BR700–710A2–
20 turbofan engines of the affected
design in the worldwide fleet. We
estimate that 400 engines installed on
airplanes of U.S. registry would be
affected by this proposed AD. We also
estimate that it would take about 7 work
hours per engine to perform the
inspections, and that the average labor
rate is $65 per work hour. We estimate
the total labor cost for performing one
inspection of the U.S. fleet to be
$182,000. New design fan discs and fan
blades would cost about $150,000 per
engine. Based on these figures, the total
cost of the proposed AD on U.S.
operators is estimated to be $60,182,000.
The manufacturer has stated that it may
provide the new fan disc and new fan
blades at no cost to operators.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
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We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD 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.
For the reasons discussed above, I
certify that the 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. Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this proposal and placed
it in the AD Docket. You may get a copy
of this summary by sending a request to
us at the address listed under
ADDRESSES. Include ‘‘AD Docket No.
2000–NE–48–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13107 (68 FR
17727, April 11, 2003) and by adding a
new airworthiness directive, to read as
follows:
Rolls-Royce Deutschland Ltd & Co KG
(formerly Rolls-Royce Deutschland
GmbH, formerly BMW Rolls-Royce
GmbH): Docket No. 2000–NE–48–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
September 6, 2005.
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Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Proposed Rules
Affected ADs
(b) This AD supersedes AD 2003–07–11,
Amendment 39–13107.
Applicability
(c) This AD applies to Rolls-Royce
Deutschland Ltd & Co KG (RRD) (formerly
Rolls-Royce Deutschland GmbH, formerly
BMW Rolls-Royce GmbH) models BR700–
710A1–10 and BR700–710A2–20 turbofan
engines. These engines are installed on, but
not limited to, Bombardier Inc. BD–700–
1A10, BD–700–1A11, and Gulfstream
Aerospace Corp. G–V series airplanes.
Unsafe Condition
(d) This AD results from a revised RRD
service bulletin (SB) that introduces relaxed
inspection intervals for certain P/N
combinations of fan discs and fan blades, and
introduces improved design fan discs and fan
blades. The actions specified in this AD are
intended to detect and prevent cracks in the
fan disc that could result in an uncontained
engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Initial Inspection
Engines With Fan Disc P/N BRR18803 or
BRR19248 Installed and Fan Blades P/N
BRR20677 or BRR23178 Installed
(f) For engines with fan disc P/N BRR18803
or BRR19248 installed, and fan blades P/N
BRR20677 or BRR23178 installed, do the
following:
(1) If the last fan disc inspection was a
visual inspection performed using RRD SB
No. SB–BR700–72–900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20,
2001; Revision 5, dated January 8, 2003; or
Revision 6, dated February 23, 2005, visually
or ultrasonically inspect fan disc within 25
flight cycles-since-last inspection (CSLI). Use
paragraphs A through F of the applicable Part
1 or Part 2 of the Accomplishment
Instructions of RRD SB No. SB–BR700–72–
900229, Revision 6, dated February 23, 2005
to do the inspection.
(2) If the last fan disc inspection was an
ultrasonic inspection performed using RRD
SB No. SB–BR700–72–900229, Revision 3,
dated July 12, 2001; Revision 4, dated
December 20, 2001; Revision 5, dated January
8, 2003; or Revision 6, dated February 23,
2005, visually or ultrasonically inspect fan
disc within 75 CSLI. Use paragraphs A
through F of the applicable Part 1 or Part 2
of the Accomplishment Instructions of RRD
SB No. SB–BR700–72–900229, Revision 6,
dated February 23, 2005 to do the inspection.
(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. Use paragraphs A
through F of the applicable Part 1 or Part 2
of the Accomplishment Instructions of RRD
SB No. SB–BR700–72–900229, Revision 6,
dated February 23, 2005 to do the inspection.
(4) If any cracks are found, remove the disc
from service and replace with a serviceable
disc.
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Engines With Fan Disc P/N BRR20791
Installed, and Fan Blades P/N BRR20677 or
BRR23178 Installed
(g) For BR700–710A1–10 engines with
serial numbers (SNs) 11452 and lower, and
BR700–710A2–20 engines with SNs 12352
and lower, with fan disc P/N BRR20791
installed, and fan blades P/N BRR20677 or
BRR23178 installed, do the following:
(1) If the last fan disc inspection was a
visual inspection performed using RRD SB
No. SB–BR700–72–900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20,
2001; Revision 5, dated January 8, 2003; or
Revision 6, dated February 23, 2005, visually
or ultrasonically inspect fan disc within 25
CSLI. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No.
SB–BR700–72–900229, Revision 6, dated
February 23, 2005 to do the inspection.
(2) If the last fan disc inspection was an
ultrasonic inspection performed using RRD
SB No. SB–BR700–72–900229, Revision 3,
dated July 12, 2001; Revision 4, dated
December 20, 2001; Revision 5, dated January
8, 2003; or Revision 6, dated February 23,
2005, visually or ultrasonically inspect fan
disc within 150 CSLI. Use paragraphs A
through F of the applicable Part 1 or Part 2
of the Accomplishment Instructions of RRD
SB No. SB–BR700–72–900229, Revision 6,
dated February 23, 2005 to do the inspection.
(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. Use paragraphs A
through F of the applicable Part 1 or Part 2
of the Accomplishment Instructions of RRD
SB No. SB–BR700–72–900229, Revision 6,
dated February 23, 2005 to do the inspection.
(4) If any cracks are found, remove the disc
from service and replace with a serviceable
disc.
(h) 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). Use paragraphs A through F of the
applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No.
SB–BR700–72–900229, Revision 5, dated
January 8, 2003; or Revision 6, dated
February 23, 2005 to do the inspection.
(2) If any cracks are found, remove the disc
from service and replace with a serviceable
disc.
Repetitive Inspections
(i) Except for engines listed in paragraph (j)
of this AD, perform repetitive inspections
using the criteria in paragraphs (f) through
(g)(4), and (k) of this AD.
(j) 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 (g)(1), (g)(2), (g)(4), and (k) of this
AD.
(k) For fan discs P/Ns BRR18803,
BRR19248, and BRR20791, with fan blades
P/N BRR20677 or BRR23178 installed, do the
following:
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38629
(1) Perform a visual and ultrasonic
inspection before accumulating 500 hourssince-new. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No.
SB–BR700–72–900229, Revision 5, dated
January 8, 2003, or Revision 6, dated
February 23, 2005 to do the inspection.
(2) Thereafter, perform a visual and an
ultrasonic inspection before accumulating
500 hours since the last visual or ultrasonic
inspection.
Engines With Fan Disc P/N BRR20791
Installed, and Fan Blades P/N FW33513,
FW33980, FW33925, FW34114, or FW34776
Installed
(1) For engines with fan disc P/N
BRR20791, BRR24829, or FW33929 installed,
and fan blades P/N FW33513, FW33980,
FW33925, FW34114, or FW34776 installed,
do the following:
Initial Inspection
(1) Perform a visual and ultrasonic
inspection of the fan disc at time of
installation of new fan blades P/N FW33513,
FW33980, FW33925, FW34114, or FW34776.
Use paragraphs A through F of the applicable
Part 1 or Part 2 of the Accomplishment
Instructions of RRD SB No. SB–BR700–72–
900229, Revision 6, dated February 23, 2005
to do the inspection.
(2) If any cracks are found, remove the disc
from service and replace with a serviceable
disc.
Repetitive Inspections
(3) Perform a visual and ultrasonic
inspection of the fan disc within 375 flight
CSLI or 600 flight hours since-lastinspection, whichever occurs first. Use
paragraphs A through F of the applicable Part
1 or Part 2 of the Accomplishment
Instructions of RRD SB No. SB–BR700–72–
900229, Revision 6, dated February 23, 2005
to do the inspection; and
(4) Repeat the fan disc visual and
ultrasonic inspection within 750 flight CSLI
or 1,100 flight hours since-last-inspection,
whichever occurs first. Use paragraphs A
through F of the applicable Part 1 or Part 2
of the Accomplishment Instructions of RRD
SB No. SB–BR700–72–900229, Revision 6,
dated February 23, 2005 to do the inspection;
and
(5) Thereafter, perform repetitive visual
and ultrasonic inspections of the fan disc
within every 1,500 flight CSLI or 2,200 flight
hours since-last-inspection, whichever
occurs first. Use paragraphs A through F of
the applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No.
SB–BR700–72–900229, Revision 6, dated
February 23, 2005 to do the inspection.
(6) If any cracks are found, remove disc
from service and replace with a serviceable
disc.
Optional Terminating Action
(m) Installation of a new fan disc P/N
FW33927, new fan blades,
P/N FW33513, or P/N FW33980, and N1
Keep Out Zone software with EEC P/Ns
1501KDC02–010, or 1501KDC03–010, or
1501KDC05–010, or 1520KDC05–010, or
1520KDC05R–010, or 1520KDC07–010, or
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1520KDC08–010, is optional terminating
action to the repetitive inspections required
by this AD.
Inspection Reporting Requirements
(n) 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
(o) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(p) LBA airworthiness directive 2000–348,
Revision 6, dated March 31, 2005, also
addresses the subject of this AD.
Issued in Burlington, Massachusetts, on
June 28, 2005.
Diane S. Romanosky,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–13135 Filed 7–1–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21712; Directorate
Identifier 2005–NM–070–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737 airplanes.
This proposed AD would require
modifying the elevator input torque tube
assembly. This proposed AD is
prompted by a report of a restriction in
the pilots’ elevator input control system.
We are proposing this AD to prevent
loss of elevator control and consequent
reduced controllability of the airplane.
DATES: We must receive comments on
this proposed AD by August 19, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
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15:08 Jul 01, 2005
Jkt 205001
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, PO Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21712; the directorate identifier for this
docket is 2005–NM–070–AD.
FOR FURTHER INFORMATION CONTACT:
Douglas Tsuji, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6487; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21712; Directorate Identifier
2005–NM–070–AD’’ in the subject line
of your comments. We specifically
invite comments on the overall
regulatory, economic, environmental,
and energy aspects of the proposed AD.
We will consider all comments
submitted by the closing date and may
amend the proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review DOT’s complete Privacy Act
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
We have received a report of a
restriction in the pilots’ elevator input
control system on a Boeing Model 737–
700 series airplane. As part of the
incident investigation, a design review
of the input torque tube assembly for the
power control unit (PCU) showed that,
in several locations, a single broken bolt
or backed-off nut, and subsequent
migration of the fastener, could jam the
torque tube. This condition, if not
corrected, could result in loss of
elevator control and consequent
reduced controllability of the airplane.
Similar Models
The torque tube assembly on Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes is
similar to that on the affected Boeing
Model 737–700 series airplane; and the
torque tube assembly on certain Boeing
Model 737–600, –700C, –800 and –900
series airplanes is similar or identical to
that on the affected Boeing Model 737–
700 series airplanes. Therefore, all of
these models may be subject to the same
unsafe condition.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–27A1271,
including Appendix A, dated December
16, 2004 (for Boeing Model 737–600,
–700, –700C, –800 and –900 series
airplanes); and Boeing Alert Service
Bulletin 737–27A1274, including
Appendix A, dated February 17, 2005
(for Boeing Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes). These service bulletins
describe procedures for modifying the
elevator input torque tube assembly. For
all airplanes, the modification includes
installing a new blind bolt in both the
left and right horizontal cable
quadrants; and installing a new shroud
to cover the PCU reaction link ground
E:\FR\FM\05JYP1.SGM
05JYP1
]]>Agencies
[Federal Register Volume 70, Number 127 (Tuesday, July 5, 2005)]
[Proposed Rules]
[Pages 38627-38630]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13135]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-48-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
(Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH)
Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly
Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) models
BR700-710A1-10 and BR700-710A2-20 turbofan engines. That AD currently
requires initial and repetitive visual and ultrasonic inspections of
fan discs, part numbers (P/Ns) BRR18803, BRR19248, and BRR20791 for
cracks, and if necessary, replacement with serviceable parts. This
proposed AD would require the same inspections of these fan discs, with
certain old design P/N fan blades installed. This proposed AD would
extend the inspection interval for certain fan discs having new design
P/N fan blades installed. Also, this proposed AD would add as optional
terminating action to the repetitive inspections, installation of
certain P/N new fan discs, certain P/N new fan blades, and engine fan
speed (N1) Keep Out Zone software. This proposed AD results from a
revised RRD service bulletin (SB) that introduces relaxed inspection
intervals for certain P/N combinations of fan discs and fan blades, and
introduces improved design fan discs and fan blades. We are proposing
this AD to detect and prevent cracks in the fan disc that could result
in an uncontained engine failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by September 6,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: 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.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 15827
Blankenfelde-Mahlow, Germany, telephone: International Access Code 011,
Country Code 49, (0) 33-7086-1768, fax: International Access Code 011,
Country Code 49, (0) 33-7086-3356.
You may examine the AD docket, by appointment, at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone: (781)
238-7747, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-48-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by the closing date and may amend the proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On April 1, 2003, the FAA issued AD 2003-07-11, Amendment 39-13107
(68 FR 17727, April 11, 2003). That AD requires initial and repetitive
visual and ultrasonic inspections of fan discs, P/Ns BRR18803,
BRR19248, and BRR20791,
[[Page 38628]]
for cracks, and if necessary, replacement with serviceable parts.
Actions Since AD 2003-07-11 Was Issued
Since AD 2003-07-11 was issued, RRD has reevaluated the existing
repetitive inspection interval requirements, and has introduced new
design fan discs and fan blades.
Relevant Service Information
We have reviewed and approved the technical contents of RRD SB No.
SB-BR700-72-900229, Revision 6, dated February 23, 2005, that describes
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. That SB also introduces
the installation of a new design fan disc and new design fan blades.
The Luftfahrt-Bundesamt (LBA), which is the aviation authority for
Germany, classified this service bulletin as mandatory and issued AD
2000-348, Revision 6, dated March 31, 2005, 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 the Proposed AD and the Service Information
Although the visual inspection requirements of RRD SB No. SB-BR700-
72-900229, Revision 6, dated February 23, 2005, do not specifically
define the pass or fail criteria for fan discs, this proposed AD would
specifically instruct the rejection of fan discs that have visual
cracks. We communicated with RRD and 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. We
subsequently reviewed the maintenance manuals and confirmed that no
cracks are allowed in the fan discs.
Bilateral Agreement Information
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. In keeping with this
bilateral airworthiness agreement, the LBA has kept the FAA informed of
the situation described above. We have 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 and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require:
For fan disc P/N BRR18803, BRR19248, BRR20791, BRR24829,
BRR24829, or FW33929 installed, initial and repetitive inspections for
cracks.
As optional terminating action to the repetitive
inspection requirements of the proposed AD, installation of a new fan
disc P/N FW33927, new fan blades P/N FW33513 or P/N FW33980, and N1
Keep Out Zone software.
The proposed AD would require that you do the inspections using the
service information described previously.
Costs of Compliance
There are about 500 RRD models BR700-710A1-10 and BR700-710A2-20
turbofan engines of the affected design in the worldwide fleet. We
estimate that 400 engines installed on airplanes of U.S. registry would
be affected by this proposed AD. We also estimate that it would take
about 7 work hours per engine to perform the inspections, and that the
average labor rate is $65 per work hour. We estimate the total labor
cost for performing one inspection of the U.S. fleet to be $182,000.
New design fan discs and fan blades would cost about $150,000 per
engine. Based on these figures, the total cost of the proposed AD on
U.S. operators is estimated to be $60,182,000. The manufacturer has
stated that it may provide the new fan disc and new fan blades at no
cost to operators.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2000-NE-48-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-13107 (68 FR
17727, April 11, 2003) and by adding a new airworthiness directive, to
read as follows:
Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. 2000-
NE-48-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by September 6,
2005.
[[Page 38629]]
Affected ADs
(b) This AD supersedes AD 2003-07-11, Amendment 39-13107.
Applicability
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD)
(formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce
GmbH) models BR700-710A1-10 and BR700-710A2-20 turbofan engines.
These engines are installed on, but not limited to, Bombardier Inc.
BD-700-1A10, BD-700-1A11, and Gulfstream Aerospace Corp. G-V series
airplanes.
Unsafe Condition
(d) This AD results from a revised RRD service bulletin (SB)
that introduces relaxed inspection intervals for certain P/N
combinations of fan discs and fan blades, and introduces improved
design fan discs and fan blades. The actions specified in this AD
are intended to detect and prevent cracks in the fan disc that could
result in an uncontained engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Inspection
Engines With Fan Disc P/N BRR18803 or BRR19248 Installed and Fan
Blades P/N BRR20677 or BRR23178 Installed
(f) For engines with fan disc P/N BRR18803 or BRR19248
installed, and fan blades P/N BRR20677 or BRR23178 installed, do the
following:
(1) If the last fan disc inspection was a visual inspection
performed using RRD SB No. SB-BR700-72-900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20, 2001; Revision 5,
dated January 8, 2003; or Revision 6, dated February 23, 2005,
visually or ultrasonically inspect fan disc within 25 flight cycles-
since-last inspection (CSLI). Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 6, dated February 23, 2005
to do the inspection.
(2) If the last fan disc inspection was an ultrasonic inspection
performed using RRD SB No. SB-BR700-72-900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20, 2001; Revision 5,
dated January 8, 2003; or Revision 6, dated February 23, 2005,
visually or ultrasonically inspect fan disc within 75 CSLI. Use
paragraphs A through F of the applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No. SB-BR700-72-900229,
Revision 6, dated February 23, 2005 to do the inspection.
(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. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 6, dated February 23, 2005
to do the inspection.
(4) If any cracks are found, remove the disc from service and
replace with a serviceable disc.
Engines With Fan Disc P/N BRR20791 Installed, and Fan Blades P/N
BRR20677 or BRR23178 Installed
(g) For BR700-710A1-10 engines with serial numbers (SNs) 11452
and lower, and BR700-710A2-20 engines with SNs 12352 and lower, with
fan disc P/N BRR20791 installed, and fan blades P/N BRR20677 or
BRR23178 installed, do the following:
(1) If the last fan disc inspection was a visual inspection
performed using RRD SB No. SB-BR700-72-900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20, 2001; Revision 5,
dated January 8, 2003; or Revision 6, dated February 23, 2005,
visually or ultrasonically inspect fan disc within 25 CSLI. Use
paragraphs A through F of the applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No. SB-BR700-72-900229,
Revision 6, dated February 23, 2005 to do the inspection.
(2) If the last fan disc inspection was an ultrasonic inspection
performed using RRD SB No. SB-BR700-72-900229, Revision 3, dated
July 12, 2001; Revision 4, dated December 20, 2001; Revision 5,
dated January 8, 2003; or Revision 6, dated February 23, 2005,
visually or ultrasonically inspect fan disc within 150 CSLI. Use
paragraphs A through F of the applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No. SB-BR700-72-900229,
Revision 6, dated February 23, 2005 to do the inspection.
(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. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 6, dated February 23, 2005
to do the inspection.
(4) If any cracks are found, remove the disc from service and
replace with a serviceable disc.
(h) 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). Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 5, dated January 8, 2003; or
Revision 6, dated February 23, 2005 to do the inspection.
(2) If any cracks are found, remove the disc from service and
replace with a serviceable disc.
Repetitive Inspections
(i) Except for engines listed in paragraph (j) of this AD,
perform repetitive inspections using the criteria in paragraphs (f)
through (g)(4), and (k) of this AD.
(j) 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 (g)(1), (g)(2), (g)(4), and (k) of this AD.
(k) For fan discs P/Ns BRR18803, BRR19248, and BRR20791, with
fan blades P/N BRR20677 or BRR23178 installed, do the following:
(1) Perform a visual and ultrasonic inspection before
accumulating 500 hours-since-new. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 5, dated January 8, 2003, or
Revision 6, dated February 23, 2005 to do the inspection.
(2) Thereafter, perform a visual and an ultrasonic inspection
before accumulating 500 hours since the last visual or ultrasonic
inspection.
Engines With Fan Disc P/N BRR20791 Installed, and Fan Blades P/N
FW33513, FW33980, FW33925, FW34114, or FW34776 Installed
(1) For engines with fan disc P/N BRR20791, BRR24829, or FW33929
installed, and fan blades P/N FW33513, FW33980, FW33925, FW34114, or
FW34776 installed, do the following:
Initial Inspection
(1) Perform a visual and ultrasonic inspection of the fan disc
at time of installation of new fan blades P/N FW33513, FW33980,
FW33925, FW34114, or FW34776. Use paragraphs A through F of the
applicable Part 1 or Part 2 of the Accomplishment Instructions of
RRD SB No. SB-BR700-72-900229, Revision 6, dated February 23, 2005
to do the inspection.
(2) If any cracks are found, remove the disc from service and
replace with a serviceable disc.
Repetitive Inspections
(3) Perform a visual and ultrasonic inspection of the fan disc
within 375 flight CSLI or 600 flight hours since-last-inspection,
whichever occurs first. Use paragraphs A through F of the applicable
Part 1 or Part 2 of the Accomplishment Instructions of RRD SB No.
SB-BR700-72-900229, Revision 6, dated February 23, 2005 to do the
inspection; and
(4) Repeat the fan disc visual and ultrasonic inspection within
750 flight CSLI or 1,100 flight hours since-last-inspection,
whichever occurs first. Use paragraphs A through F of the applicable
Part 1 or Part 2 of the Accomplishment Instructions of RRD SB No.
SB-BR700-72-900229, Revision 6, dated February 23, 2005 to do the
inspection; and
(5) Thereafter, perform repetitive visual and ultrasonic
inspections of the fan disc within every 1,500 flight CSLI or 2,200
flight hours since-last-inspection, whichever occurs first. Use
paragraphs A through F of the applicable Part 1 or Part 2 of the
Accomplishment Instructions of RRD SB No. SB-BR700-72-900229,
Revision 6, dated February 23, 2005 to do the inspection.
(6) If any cracks are found, remove disc from service and
replace with a serviceable disc.
Optional Terminating Action
(m) Installation of a new fan disc P/N FW33927, new fan blades,
P/N FW33513, or P/N FW33980, and N1 Keep Out Zone software with EEC
P/Ns 1501KDC02-010, or 1501KDC03-010, or 1501KDC05-010, or
1520KDC05-010, or 1520KDC05R-010, or 1520KDC07-010, or
[[Page 38630]]
1520KDC08-010, is optional terminating action to the repetitive
inspections required by this AD.
Inspection Reporting Requirements
(n) 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
(o) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(p) LBA airworthiness directive 2000-348, Revision 6, dated
March 31, 2005, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on June 28, 2005.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-13135 Filed 7-1-05; 8:45 am]
BILLING CODE 4910-13-P
