[Federal Register: October 25, 2007 (Volume 72, Number 206)]
[Proposed Rules]
[Page 60606-60609]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25oc07-28]
-----------------------------------------------------------------------
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 http://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 http://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 http://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