Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 60606-60609 [E7-20999]
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60606
Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
Instructions, of MRAS ASB No. CF6–
80C2A1/A2/A3/A5/A8/A5F S/B 78A1015,
Revision 7, dated August 30, 2007, at the
following:
(1) On Airbus A300 and A310 series
airplanes with left-hand and right-hand
reverser halves that do not have the double/
backup P-seal introduced by MRAS SB No.
CF6–80C2 S/B 78A1005, and that do not
have locking actuator assemblies (LAAs)
installed, within 600 hours TIS after the
effective date of this AD.
(2) On Airbus A300 and A310 series
airplanes with left-hand and right-hand
reverser halves that have the double/backup
P-seal introduced by MRAS SB No. CF6–
80C2 S/B 78A1005, or that have LAAs
installed, within 7,000 hours TIS after the
effective date of this AD.
Directional Pilot Valve (DPV) Pressure
Switch Check on Airbus Airplanes With
CF6–80C2A5F Engines Is Not Applicable
(3) The DPV pressure switch check per
paragraph 2.F. is not applicable to Airbus
airplanes with CF6–80C2A5F left-hand and
right-hand fan reverser halves (model ES–
CF6–5), because this check is performed
through the full authority digital electronic
control fault detection system.
(3) MRAS ASB No. CF6–80C2 S/B
78A1015, Revision 5, dated January 21, 1999;
and MRAS ASB No. CF6–80C2A1/A2/A3/
A5/A8/A5F S/B 78A1015, Revision 6, dated
May 3, 2006.
Alternative Methods of Compliance
(m) The Manager, Engine Certification
Office, FAA, 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
(n) France AD 1999–422– IMP(B), dated
October 20, 1999, also addresses the subject
of this AD.
(o) Contact Robert Green, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: Robert.green@faa.gov;
telephone (781) 238–7754; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
October 18, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–21000 Filed 10–24–07; 8:45 am]
BILLING CODE 4910–13–P
Engines That Fail an Inspection or Check
(k) On engines that fail an inspection or
check required by this AD, perform
corrective actions or deactivate the fan
reverser per Section 2, Accomplishment
Instructions, of the applicable MRAS ASB,
before further flight.
pwalker on PROD1PC71 with PROPOSALS
Repetitive Inspections for CF6–80C2A Series
Turbofan Engines
(j) For CF6–80C2A series turbofan engines,
perform repetitive thrust reverser inspections
using Section 2, Accomplishment
Instructions, of MRAS ASB No. CF6–
80C2A1/A2/A3/A5/A8/A5F S/B 78A1015,
Revision 7, dated August 30, 2007, at the
following:
(1) On Airbus A300 and A310 series
airplanes with left-hand and right-hand
reverser halves that do not have the double/
backup P-seal, introduced by MRAS SB No.
CF6–80C2 S/B 78A1005, and that do not
have LAAs installed, within every 600 hours
TSLI.
(2) On Airbus A300 and A310 series
airplanes with left-hand and right-hand
reverser halves that have the double/backup
P-seal, introduced by MRAS SB No. CF6–
80C2 S/B 78A1015, or that have LAAs
installed, within every 7,000 hours TSLI.
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce plc (RR)
RB211–535E4–37, RB211–535E4–B–37,
and RB211–535E4–B–75 series turbofan
engines. That AD requires initial and
repetitive ultrasonic inspections of
installed low pressure compressor (LPC)
fan blade roots on-wing and during
overhaul, and relubrication according to
accumulated life cycles. That AD also
introduces an alternative technique to
ultrasonically inspect installed fan
blades on-wing using a surface wave
ultrasonic probe. Also, that AD
introduces application of Metco 58
blade root coating as an optional
terminating action. This proposed AD
would require the same actions but
would add compliance paragraphs to
Previous Credit
(l) Initial and repetitive inspections and
checks of the thrust reverser actuation
systems done before the effective date of this
AD that use the following ASBs, comply with
the requirements specified in this AD:
(1) MRAS ASB No. CF6–50 S/B 78A–3001,
Revision 2, dated December 18, 1997; and
MRAS ASB No. CF6–50 S/B 78A–3001,
Revision 3, dated May 3, 2006.
(2) MRAS ASB No. CF6–80A1/A3 S/B
78A–1002, Revision 3, dated January 21,
1999; and MRAS ASB No. CF6–80A1/A3 S/
B 78A–1002, Revision 4, dated May 3, 2006.
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29343; Directorate
Identifier 2000–NE–13–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
PO 00000
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relax the compliance schedule for
repetitive inspections for RB211–535E4
engines operating in flight profiles A
and B, if certain requirements are met.
This proposed AD results from RR
issuing Mandatory Service Bulletin
(MSB) No. RB.211–72–C879, Revision 5.
That MSB introduces a relaxed
repetitive compliance schedule for
RB211–535E4 engines operating in
flight profiles A and B, if certain
requirements are met. We are proposing
this AD to detect cracks in LPC fan
blade roots, which if not detected, could
lead to uncontained multiple fan blade
failure, and damage to the airplane.
DATES: We must receive any comments
on this proposed AD by December 24,
2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• 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,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
Contact Rolls-Royce plc, PO Box 31,
Derby, England, DE248BJ; telephone:
011–44–1332–242–424; fax: 011–44–
1332–249–936 for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Ian
Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; e-mail: ian.dargin@faa.gov;
telephone: (781) 238–7178; fax: (781)
238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2007–29343; Directorate Identifier
2000–NE–13–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 received by the
closing date and may amend the
proposed AD in light of those
comments.
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Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
We will post all comments we
receive, without change, to https://
www.regulations.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 the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
Discussion
On January 18, 2005, we issued AD
2005–02–05, Amendment 39–13950 (70
FR 3863, January 27, 2005). That AD
requires initial and repetitive ultrasonic
inspections of installed LPC fan blade
roots on-wing and during overhaul
using a surface wave ultrasonic probe,
and relubrication according to
accumulated life cycles. That AD also
adds the application of Metco 58 blade
root coating as an optional terminating
action. That AD results from RR issuing
MSB No. RB.211–72–C879, Revision 4,
which contains revised
Accomplishment Instructions and
consumable materials list.
pwalker on PROD1PC71 with PROPOSALS
Actions Since We Issued AD 2005–02–
05
Since we issued AD 2005–02–05,
Rolls-Royce plc updated MSB No.
RB.211–72–C879, Revision 4, dated
April 2, 2004, to Revision 5, dated
March 8, 2007, for RR RB211 series
turbofan engines. Revision 5 relaxes the
compliance for repetitive inspections for
RB211–535E4 engines operating in
flight profiles A and B, if certain
requirements are met.
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
Clarification Changes
Also, as clarification, we changed the
Table 4 initial compliance from ‘‘65%
hard life’’ to ‘‘within 350 cycles after
achieving 65% hard life’’. These
changes better reflect the proposed AD
wording, with the latest MSB.
Relevant Service Information
We have reviewed and approved the
technical contents of Rolls-Royce plc
MSB No. RB.211–72–C879, Revision 5,
dated March 8, 2007. That MSB
describes procedures for ultrasonic
inspection of high cyclic life blades onwing with either the LPC fan blades in
place or removed from the LPC. The
Civil Aviation Authority (CAA), which
is the airworthiness authority for the
United Kingdom (UK), classified the
original issue of the service bulletin as
mandatory and issued AD 002–01–2000
to ensure the airworthiness of these RR
engines in the UK.
Bilateral Agreement Information
This engine model is manufactured in
UK 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. Under this
bilateral airworthiness agreement, the
UK kept us informed of the situation
described above. We have examined the
findings of the CAA, 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. We are proposing this AD,
which would require initial and
repetitive ultrasonic inspection of
installed LPC fan blade roots on-wing
and during overhaul using a surface
wave ultrasonic probe, and relubrication
according to accumulated life cycles.
This proposed AD would also maintain
the application of Metco 58 blade root
coating as an optional terminating
action. The proposed AD would require
that you do these actions using the
service information described
previously.
Costs of Compliance
We estimate that this proposed AD
would affect 788 engines installed on
airplanes of U.S. registry. We also
estimate that it would take about 7
work-hours per engine to perform the
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60607
proposed actions, and that the average
labor rate is $80 per work-hour. Based
on these figures, we estimate the total
cost of the proposed AD to U.S.
operators to be $358,540.
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 AD:
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
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
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60608
Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
3863, January 27, 2005) and by adding
a new airworthiness directive, to read as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
RB211–535E4–37, RB211–535E4–B–37, and
RB211–535E4–B–75 series turbofan engines
with low pressure compressor (LPC) fan
blades with the part numbers (P/Ns) listed in
Table 1 of this AD. These engines are
installed on, but not limited to, Boeing 757
and Tupolev Tu204 series airplanes. Table 1
follows:
Comments Due Date
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Affected ADs
(b) This AD revises AD 2005–02–05,
Amendment 39–13950.
Rolls-Royce plc: Docket No. FAA–2007–
29343; Directorate Identifier 2000–NE–
13–AD.
proposes to amend 14 CFR part 39 as
follows:
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13950 (70 FR
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
December 24, 2007.
TABLE 1.—APPLICABLE LPC FAN BLADE P/NS
UL16135
UL20132
UL24525
UL27992
UL30817
UL33709
UL37276
UL16171
UL20616
UL24528
UL28601
UL30819
UL36992
UL37278
UL16182
UL21345
UL24530
UL28602
UL30933
UL37090
UL38029
Unsafe Condition
(d) This AD results from RR issuing
Mandatory Service Bulletin (MSB) No.
RB.211–72–C879, Revision 5, that introduces
a relaxed repetitive compliance schedule for
RB211–535E4 engines operating in flight
profiles A and B, if certain requirements are
met. We are issuing this AD to detect cracks
in low pressure compressor (LPC) fan blade
roots, which if not detected, could lead to
UL19643
UL22286
UL24532
UL29511
UL30935
UL37272
UL38032
uncontained multiple fan blade 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) If you have a full set of fan blades,
modified using RR Service Bulletin No.
UL20044
UL23122
UL24534
UL29556
UL33707
UL37274
RB.211–72–C946, Revision 2, dated
September 26, 2002, that can be identified by
a blue triangle etched on the blade airfoil
suction surface close to the leading edge tip
of each blade, no further action is required.
(g) On RB211–535E4 engines, operated to
Flight Profile A, ultrasonically inspect, and if
required, relubricate using the following
Table 2:
TABLE 2.—RB211–535E4 FLIGHT PROFILE A
Engine location
Initial inspection
within cycles-sincenew
(CSN)
(1) On-wing ........
17,350
In accordance with mandatory service
bulletin
(MSB)
Type action
(i) Root Probe, inspect and relubricate, OR
(ii) Wave Probe ..................................
(2) In Shop .........
17,350
Root Probe, inspect and relubricate ..
(h) On RB211–535E4 engines, operated to
Flight Profile B, ultrasonically inspect, and if
RB.211–72–C879 Revision
through 3.A.(7), dated
2007.
RB.211–72–C879 Revision
through 3.B.(7), dated
2007.
RB.211–72–C879 Revision
through 3.C.(4), dated
2007.
Repeat inspection
within
(CSN)
5, 3.A.(1)
March 8,
1,400
5, 3.B.(1)
March 8,
1,150
5, 3.C.(1)
March 8,
1,400
required, relubricate using the following
Table 3:
TABLE 3.—RB211–535E4 FLIGHT PROFILE B
Engine location
Initial inspection
within
(CSN)
pwalker on PROD1PC71 with PROPOSALS
(1) On-wing ........
12,350
Type action
In accordance with MSB
(i) Root Probe, inspect and relubricate,
OR
(ii) Wave Probe ....................................
(2) In Shop .........
VerDate Aug<31>2005
17:49 Oct 24, 2007
12,350
Jkt 214001
Root Probe, inspect and relubricate ....
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RB.211–72–C879 Revision
through 3.A.(7), dated
2007.
RB.211–72–C879 Revision
through 3.B.(7), dated
2007.
RB.211–72–C879 Revision
through 3.C.(4), dated
2007.
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Repeat inspection
within
(CSN)
5, 3.A.(1)
March 8,
850
5, 3.B.(1)
March 8,
700
5, 3.C.(1)
March 8,
850
Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
(i) On RB211–535E4 engines, operated to
combined Flight Profile A and B,
60609
ultrasonically inspect, and if required,
relubricate using the following Table 4:
TABLE 4.—RB211–535E4 FLIGHT PROFILE A AND B
Engine location
(1) On-wing .......
Initial inspection within
(CSN)
Type action
(i) Root Probe, inspect and
relubricate, OR
350 cycles after achieving
65% hard life (To calculate, see MSB Compliance Section 1.C.(4)).
(j) For RB.211–535E4 engines that are
currently flying in Profile A, if the initial
inspection is completed before X minus
1,400 cycles then the next inspection may be
delayed to X, where X is 65% of the revised
life limit.
(k) For RB.211–535E4 engines that are
currently flying in Profile B, if the initial
RB.211–72–C879 Revision 5,
3.A.(1) through 3.A.(7),
dated March 8, 2007.
As current flight profile. See
paragraphs (j) and (k) of
this AD.
(ii) Wave Probe .....................
(2) In Shop ........
350 cycles after achieving
65% hard life (To calculate, see MSB Compliance Section 1.C.(4)).
Repeat inspection within
(CSN)
In accordance with MSB
RB.211–72–C879 Revision 5,
3.B.(1) through 3.B.(7),
dated March 8, 2007.
RB.211–72–C879 Revision 5,
3.C.(1) through 3.C.(4),
dated March 8, 2007.
As current flight profile. See
paragraphs (j) and (k) of
this AD.
As current flight profile. See
paragraphs (j) and (k) of
this AD.
Root Probe, inspect and relubricate.
inspection is completed before X minus 850
cycles then the next inspection may be
delayed to X, where X is 65% of the revised
life limit.
(l) Fan blades that have been operated
within RB.211–535E4 Flight Profile A and B
will have final life as defined in the Time
Limits Manual. See References Section
1.G.(3), of MSB RB.211–72–C879, Revision 5,
dated March 8, 2007.
(m) On RB.211–535E4–B engines,
ultrasonically inspect, and if required,
relubricate using the following Table 5:
TABLE 5.—RB211–535E4–B
Engine location
Initial inspection
within
(CSN)
(1) On-wing ........
17,000
Type action
In accordance with MSB
(i) Root Probe, inspect and relubricate,
OR
(ii) Wave Probe ....................................
(2) In Shop .........
17,000
Root Probe, inspect and relubricate ....
Optional Terminating Action
(n) Application of Metco 58 blade root
coating using RR SB No. RB.211–72–C946,
Revision 2, dated September 26, 2002,
constitutes terminating action to the
repetitive inspection requirements specified
in paragraphs (g), (h), (i), and (k) of this AD.
RB.211–72–C879 Revision
through 3.A.(7), dated
2007.
RB.211–72–C879 Revision
through 3.B.(7), dated
2007.
RB.211–72–C879 Revision
through 3.C.(4), dated
2007.
Issued in Burlington, Massachusetts, on
October 18, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–20999 Filed 10–24–07; 8:45 am]
BILLING CODE 4910–13–P
Alternative Methods of Compliance
pwalker on PROD1PC71 with PROPOSALS
(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.
Previous Credit
(p) Previous credit is allowed for initial
and repetitive inspections performed using
AD 2003–12–15 (Amendment 39–13200, 68
FR 37735, June 25, 2003), RR MSB No.
RB.211–72–C879, Revision 3, dated October
9, 2002, and RR MSB No. RB.211–72–C879,
Revision 4, dated April 2, 2004.
Related Information
(q) CAA airworthiness directive AD 002–
01–2000, dated October 9, 2002, also
addresses the subject of this AD.
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
DEPARTMENT OF COMMERCE
United States Patent and Trademark
Office
37 CFR Part 2
[Docket No. PTO–T–2007–0035]
RIN 0651–AC17
Changes in the Requirement for a
Description of the Mark in Trademark
Applications
United States Patent and
Trademark Office, Commerce.
AGENCY:
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ACTION:
Repeat inspection
within
(CSN)
5, 3.A.(1)
March 8,
1,200
5, 3.B.(1)
March 8,
1,000
5, 3.C.(1)
March 8,
1,200
Notice of proposed rulemaking.
SUMMARY: The United States Patent and
Trademark Office (‘‘USPTO’’) proposes
to amend the Rules of Practice in
Trademark Cases to require a
description of the mark in all
applications to register a mark not in
standard characters.
DATES: Comments must be received by
December 24, 2007 to ensure
consideration.
The Office prefers that
comments be submitted via electronic
mail message to TM Description
Requirements@uspto.gov. Written
comments may also be submitted by
mail to Commissioner for Trademarks,
P.O. Box 1451, Alexandria, VA 22313–
1451, attention Cynthia C. Lynch; or by
hand delivery to the Trademark
Assistance Center, Concourse Level,
James Madison Building-East Wing, 600
Dulany Street, Alexandria, Virginia,
attention Cynthia C. Lynch; or by
ADDRESSES:
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]]>Agencies
[Federal Register Volume 72, Number 206 (Thursday, October 25, 2007)]
[Proposed Rules]
[Pages 60606-60609]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-20999]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29343; Directorate Identifier 2000-NE-13-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-
37, and RB211-535E4-B-75 series turbofan engines. That AD requires
initial and repetitive ultrasonic inspections of installed low pressure
compressor (LPC) fan blade roots on-wing and during overhaul, and
relubrication according to accumulated life cycles. That AD also
introduces an alternative technique to ultrasonically inspect installed
fan blades on-wing using a surface wave ultrasonic probe. Also, that AD
introduces application of Metco 58 blade root coating as an optional
terminating action. This proposed AD would require the same actions but
would add compliance paragraphs to relax the compliance schedule for
repetitive inspections for RB211-535E4 engines operating in flight
profiles A and B, if certain requirements are met. This proposed AD
results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-
C879, Revision 5. That MSB introduces a relaxed repetitive compliance
schedule for RB211-535E4 engines operating in flight profiles A and B,
if certain requirements are met. We are proposing this AD to detect
cracks in LPC fan blade roots, which if not detected, could lead to
uncontained multiple fan blade failure, and damage to the airplane.
DATES: We must receive any comments on this proposed AD by December 24,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
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, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242-424; fax: 011-44-1332-249-936 for the
service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; e-mail:
ian.dargin@faa.gov; telephone: (781) 238-7178; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2007-29343;
Directorate Identifier 2000-NE-13-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 received by the closing date and may amend the
proposed AD in light of those comments.
[[Page 60607]]
We will post all comments we receive, without change, to https://
www.regulations.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 the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
Discussion
On January 18, 2005, we issued AD 2005-02-05, Amendment 39-13950
(70 FR 3863, January 27, 2005). That AD requires initial and repetitive
ultrasonic inspections of installed LPC fan blade roots on-wing and
during overhaul using a surface wave ultrasonic probe, and
relubrication according to accumulated life cycles. That AD also adds
the application of Metco 58 blade root coating as an optional
terminating action. That AD results from RR issuing MSB No. RB.211-72-
C879, Revision 4, which contains revised Accomplishment Instructions
and consumable materials list.
Actions Since We Issued AD 2005-02-05
Since we issued AD 2005-02-05, Rolls-Royce plc updated MSB No.
RB.211-72-C879, Revision 4, dated April 2, 2004, to Revision 5, dated
March 8, 2007, for RR RB211 series turbofan engines. Revision 5 relaxes
the compliance for repetitive inspections for RB211-535E4 engines
operating in flight profiles A and B, if certain requirements are met.
Clarification Changes
Also, as clarification, we changed the Table 4 initial compliance
from ``65% hard life'' to ``within 350 cycles after achieving 65% hard
life''. These changes better reflect the proposed AD wording, with the
latest MSB.
Relevant Service Information
We have reviewed and approved the technical contents of Rolls-Royce
plc MSB No. RB.211-72-C879, Revision 5, dated March 8, 2007. That MSB
describes procedures for ultrasonic inspection of high cyclic life
blades on-wing with either the LPC fan blades in place or removed from
the LPC. The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom (UK), classified the original issue of
the service bulletin as mandatory and issued AD 002-01-2000 to ensure
the airworthiness of these RR engines in the UK.
Bilateral Agreement Information
This engine model is manufactured in UK 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. Under this bilateral
airworthiness agreement, the UK kept us informed of the situation
described above. We have examined the findings of the CAA, 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. We are proposing this AD, which would require
initial and repetitive ultrasonic inspection of installed LPC fan blade
roots on-wing and during overhaul using a surface wave ultrasonic
probe, and relubrication according to accumulated life cycles. This
proposed AD would also maintain the application of Metco 58 blade root
coating as an optional terminating action. The proposed AD would
require that you do these actions using the service information
described previously.
Costs of Compliance
We estimate that this proposed AD would affect 788 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 7 work-hours per engine to perform the proposed actions, and
that the average labor rate is $80 per work-hour. Based on these
figures, we estimate the total cost of the proposed AD to U.S.
operators to be $358,540.
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 AD:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
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
[[Page 60608]]
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 39-13950 (70 FR
3863, January 27, 2005) and by adding a new airworthiness directive, to
read as follows:
Rolls-Royce plc: Docket No. FAA-2007-29343; Directorate Identifier
2000-NE-13-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by December 24,
2007.
Affected ADs
(b) This AD revises AD 2005-02-05, Amendment 39-13950.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211-535E4-37,
RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines with
low pressure compressor (LPC) fan blades with the part numbers (P/
Ns) listed in Table 1 of this AD. These engines are installed on,
but not limited to, Boeing 757 and Tupolev Tu204 series airplanes.
Table 1 follows:
Table 1.--Applicable LPC Fan Blade P/Ns
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
UL16135 UL16171 UL16182 UL19643 UL20044
UL20132 UL20616 UL21345 UL22286 UL23122
UL24525 UL24528 UL24530 UL24532 UL24534
UL27992 UL28601 UL28602 UL29511 UL29556
UL30817 UL30819 UL30933 UL30935 UL33707
UL33709 UL36992 UL37090 UL37272 UL37274
UL37276 UL37278 UL38029 UL38032
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from RR issuing Mandatory Service Bulletin
(MSB) No. RB.211-72-C879, Revision 5, that introduces a relaxed
repetitive compliance schedule for RB211-535E4 engines operating in
flight profiles A and B, if certain requirements are met. We are
issuing this AD to detect cracks in low pressure compressor (LPC)
fan blade roots, which if not detected, could lead to uncontained
multiple fan blade 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) If you have a full set of fan blades, modified using RR
Service Bulletin No. RB.211-72-C946, Revision 2, dated September 26,
2002, that can be identified by a blue triangle etched on the blade
airfoil suction surface close to the leading edge tip of each blade,
no further action is required.
(g) On RB211-535E4 engines, operated to Flight Profile A,
ultrasonically inspect, and if required, relubricate using the
following Table 2:
Table 2.--RB211-535E4 Flight Profile A
----------------------------------------------------------------------------------------------------------------
Initial inspection In accordance with
Engine location within cycles- Type action mandatory service Repeat inspection
since-new (CSN) bulletin (MSB) within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing........... 17,350 (i) Root Probe, RB.211-72-C879 1,400
inspect and Revision 5, 3.A.(1)
relubricate, OR through 3.A.(7),
dated March 8, 2007.
.................. (ii) Wave Probe....... RB.211-72-C879 1,150
Revision 5, 3.B.(1)
through 3.B.(7),
dated March 8, 2007.
(2) In Shop........... 17,350 Root Probe, inspect RB.211-72-C879 1,400
and relubricate. Revision 5, 3.C.(1)
through 3.C.(4),
dated March 8, 2007.
----------------------------------------------------------------------------------------------------------------
(h) On RB211-535E4 engines, operated to Flight Profile B,
ultrasonically inspect, and if required, relubricate using the
following Table 3:
Table 3.--RB211-535E4 Flight Profile B
----------------------------------------------------------------------------------------------------------------
Initial inspection Repeat inspection
Engine location within (CSN) Type action In accordance with MSB within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing............ 12,350 (i) Root Probe, inspect RB.211-72-C879 850
and relubricate, OR Revision 5, 3.A.(1)
through 3.A.(7),
dated March 8, 2007.
.................. (ii) Wave Probe........ RB.211-72-C879 700
Revision 5, 3.B.(1)
through 3.B.(7),
dated March 8, 2007.
(2) In Shop............ 12,350 Root Probe, inspect and RB.211-72-C879 850
relubricate. Revision 5, 3.C.(1)
through 3.C.(4),
dated March 8, 2007.
----------------------------------------------------------------------------------------------------------------
[[Page 60609]]
(i) On RB211-535E4 engines, operated to combined Flight Profile
A and B, ultrasonically inspect, and if required, relubricate using
the following Table 4:
Table 4.--RB211-535E4 Flight Profile A and B
----------------------------------------------------------------------------------------------------------------
Initial inspection In accordance with Repeat inspection
Engine location within (CSN) Type action MSB within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing.............. 350 cycles after (i) Root Probe, RB.211-72-C879 As current flight
achieving 65% hard inspect and Revision 5, 3.A.(1) profile. See
life (To calculate, relubricate, OR through 3.A.(7), paragraphs (j) and
see MSB Compliance dated March 8, 2007. (k) of this AD.
Section 1.C.(4)).
(ii) Wave Probe..... RB.211-72-C879 As current flight
Revision 5, 3.B.(1) profile. See
through 3.B.(7), paragraphs (j) and
dated March 8, 2007. (k) of this AD.
(2) In Shop.............. 350 cycles after Root Probe, inspect RB.211-72-C879 As current flight
achieving 65% hard and relubricate. Revision 5, 3.C.(1) profile. See
life (To calculate, through 3.C.(4), paragraphs (j) and
see MSB Compliance dated March 8, 2007. (k) of this AD.
Section 1.C.(4)).
----------------------------------------------------------------------------------------------------------------
(j) For RB.211-535E4 engines that are currently flying in
Profile A, if the initial inspection is completed before X minus
1,400 cycles then the next inspection may be delayed to X, where X
is 65% of the revised life limit.
(k) For RB.211-535E4 engines that are currently flying in
Profile B, if the initial inspection is completed before X minus 850
cycles then the next inspection may be delayed to X, where X is 65%
of the revised life limit.
(l) Fan blades that have been operated within RB.211-535E4
Flight Profile A and B will have final life as defined in the Time
Limits Manual. See References Section 1.G.(3), of MSB RB.211-72-
C879, Revision 5, dated March 8, 2007.
(m) On RB.211-535E4-B engines, ultrasonically inspect, and if
required, relubricate using the following Table 5:
Table 5.--RB211-535E4-B
----------------------------------------------------------------------------------------------------------------
Initial inspection Repeat inspection
Engine location within (CSN) Type action In accordance with MSB within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing............ 17,000 (i) Root Probe, inspect RB.211-72-C879 1,200
and relubricate, OR Revision 5, 3.A.(1)
through 3.A.(7),
dated March 8, 2007.
(ii) Wave Probe........ RB.211-72-C879 1,000
Revision 5, 3.B.(1)
through 3.B.(7),
dated March 8, 2007.
(2) In Shop............ 17,000 Root Probe, inspect and RB.211-72-C879 1,200
relubricate. Revision 5, 3.C.(1)
through 3.C.(4),
dated March 8, 2007.
----------------------------------------------------------------------------------------------------------------
Optional Terminating Action
(n) Application of Metco 58 blade root coating using RR SB No.
RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes
terminating action to the repetitive inspection requirements
specified in paragraphs (g), (h), (i), and (k) of this AD.
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.
Previous Credit
(p) Previous credit is allowed for initial and repetitive
inspections performed using AD 2003-12-15 (Amendment 39-13200, 68 FR
37735, June 25, 2003), RR MSB No. RB.211-72-C879, Revision 3, dated
October 9, 2002, and RR MSB No. RB.211-72-C879, Revision 4, dated
April 2, 2004.
Related Information
(q) CAA airworthiness directive AD 002-01-2000, dated October 9,
2002, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on October 18, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-20999 Filed 10-24-07; 8:45 am]
BILLING CODE 4910-13-P
