[Federal Register Volume 70, Number 17 (Thursday, January 27, 2005)]
[Rules and Regulations]
[Pages 3863-3867]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1384]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-13-AD; Amendment 39-13950; AD 2005-02-05]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and 
RB211-535E4-B-75 series turbofan engines. That AD currently 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. This AD requires the same actions, but changes the 
reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from 
Revision 3 to Revision 4. This AD results from RR issuing MSB No. 
RB.211-72-C879, Revision 4, which contains revised Accomplishment 
Instructions and consumable materials list. We are

[[Page 3864]]

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.

DATES: Effective February 11, 2005. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of February 11, 2005.
    We must receive any comments on this AD by March 28, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2000-NE-13-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You can get the service information referenced in this AD from 
Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-
1332-242-424; fax: 011-44-1332-249-936.
    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: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone: (781) 
238-7178; fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: On June 13, 2003, we issued AD 2003-12-15, 
Amendment 39-13200 (68 FR 37735, June 25, 2003). 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 introduces an alternative technique to ultrasonically inspect 
installed fan blades on-wing using a surface wave ultrasonic probe. 
Also, that AD adds the application of Metco 58 blade root coating as an 
optional terminating action. That AD was the result of the discovery of 
cracks on LPC fan blade roots during an engine overhaul. That 
condition, if not corrected, could result in uncontained multiple fan 
blade failure, and damage to the airplane.

Actions Since AD 2003-12-15 Was Issued

    Since AD 2003-12-15 was issued, the Civil Aviation Authority (CAA), 
which is the airworthiness authority for the United Kingdom (UK), 
notified us that Rolls-Royce plc has updated MSB No. RB.211-72-C879, 
Revision 3, dated October 3, 2002, to Revision 4, dated April 2, 2004, 
for RR RB211 series turbofan engines. The CAA advises that Revision 4 
of the MSB contains revised Accomplishment Instructions and consumable 
materials list.

Special Flight Permits Paragraph Removed

    Paragraph (h) of the current AD, AD 2003-12-15, contains a 
paragraph pertaining to special flight permits. Even though this final 
rule does not contain a similar paragraph, we have made no changes with 
regard to the use of special flight permits to operate the airplane to 
a repair facility to do the work required by this AD. In July 2002, we 
published a new part 39 that contains a general authority regarding 
special flight permits and airworthiness directives; see Docket No. 
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus, 
when we now supersede ADs we will not include a specific paragraph on 
special flight permits unless we want to limit the use of that general 
authority granted in section 39.23.

Relevant Service Information

    We have reviewed and approved the technical contents of RR MSB No. 
RB.211-72-C879, Revision 4, dated April 2, 2004. 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 
CAA classified the original issue of the service bulletin as mandatory 
and issued AD 002-01-2000 in order to ensure the airworthiness of these 
RR engines in the UK.

Bilateral Airworthiness Agreement

    These engine models are manufactured in the U.K. and are 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 CAA has kept the FAA 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 This 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 issuing this AD, which 
requires 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 AD also maintains the application of Metco 58 blade root 
coating as an optional terminating action. You must use the service 
information described previously to perform the actions required by 
this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are unnecessary, and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-13-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 rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this 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 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.

[[Page 3865]]

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD 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-13-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-13200 (68 FR 
37735, June 25, 2003), and by adding a new airworthiness directive, 
Amendment 39-13950, to read as follows:

2005-02-05 Rolls-Royce plc: Amendment 39-13950. Docket No. 2000-NE-
13-AD. Supersedes AD 2003-12-15, Amendment 39-13200.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
11, 2005.

Affected ADs

    (b) This AD supersedes AD 2003-12-15, Amendment 39-13200.

Applicability

    (c) This AD applies to Rolls-Royce (RR) plc 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                              UL28602
                UL16171                              UL29511
                UL16182                              UL29556
                UL19643                              UL30817
                UL20044                              UL30819
                UL20132                              UL30933
                UL20616                              UL30935
                UL21345                              UL33707
                UL22286                              UL33709
                UL23122                              UL36992
                UL24525                              UL37090
                UL24528                              UL37272
                UL24530                              UL37274
                UL24532                              UL37276
                UL24534                              UL37278
                UL27992                              UL38029
                UL28601                              UL38032
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from RR issuing Mandatory Service Bulletin 
(MSB) No. RB.211-72-C879, Revision 4, which contains revised 
Accomplishment Instructions and consumable materials list. 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
      Engine location        within cycles-       Type action           In accordance with     Repeat inspection
                                since-new                                                        within  (CSN)
                                  (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................          17,350  (i) Root Probe,        RB.211-72-C879 Revision                1,400
                                              inspect and            4, 3.A.(1) through
                                              relubricate, OR        3.A.(7), dated April 2,
                                                                     2004.
                             ..............  (ii) Wave Probe......  RB.211-72-C879 Revision                1,150
                                                                     4, 3.B.(1) through
                                                                     3.B.(7), dated April 2,
                                                                     2004.
(2) In Shop................          17,350  Root Probe, inspect    RB.211-72-C879 Revision                1,400
                                              and relubricate.       4, 3.C.(1) through
                                                                     3.C.(4), dated April 2,
                                                                     2004.
----------------------------------------------------------------------------------------------------------------

    (h) On RB211-535E4 engines, operated to Flight Profile B, 
ultrasonically inspect, and if required, relubricate using the 
following Table 3:

[[Page 3866]]



                                     Table 3.--RB211-535E4 Flight Profile B
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                                 Initial
      Engine location          inspection         Type action           In accordance with     Repeat inspection
                              within  (CSN)                                                      within  (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................          12,350  (i) Root Probe,        RB.211-72-C879 Revision                  850
                                              inspect and            4, 3.A.(1) through
                                              relubricate, OR        3.A.(7), dated April 2,
                                                                     2004.
                             ..............  (ii) Wave Probe......  RB.211-72-C879 Revision                  700
                                                                     4, 3.B.(1) through
                                                                     3.B.(7), dated April 2,
                                                                     2004.
(2) In Shop................          12,350  Root Probe, inspect    RB.211-72-C879 Revision                  850
                                              and relubricate.       4, 3.C.(1) through
                                                                     3.C.(4), dated April 2,
                                                                     2004.
----------------------------------------------------------------------------------------------------------------

    (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                                            Repeat inspection within
    Engine location         within  (CSN)         Type action     In accordance with             (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing...........  65% hard life (To      (i) Root Probe,   RB.211-72-C879        As current flight
                         calculate, see         inspect and       Revision 4, 3.A.(1)   profile.
                         Compliance Section     relubricate, OR   through 3.A.(7),
                         1.C(4)).                                 dated April 2, 2004.
                        .....................  (ii) Wave Probe.  RB.211-72-C879        As current flight
                                                                  Revision 4, 3.B.(1)   profile.
                                                                  through 3.B.(7),
                                                                  dated April 2, 2004.
(2) In Shop...........  65% hard life (To      Root Probe,       RB.211-72-C879        As current flight
                         calculate, see         inspect and       Revision 4, 3.C.(1)   profile.
                         Compliance Section     relubricate.      through 3.C.(4),
                         1.C.(4)).                                dated April 2, 2004.
----------------------------------------------------------------------------------------------------------------

    (j) Fan blades that have been operated within RB211-535E4 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 4, dated April 2, 2004.
    (k) On RB211-535E4-B engines, ultrasonically inspect, and if 
required, relubricate using the following Table 5:

                                             Table 5.--RB211-535E4-B
----------------------------------------------------------------------------------------------------------------
                                 Initial
      Engine location          inspection         Type action           In accordance with     Repeat inspection
                              within  (CSN)                                                      within  (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................          17,000  (i) Root Probe,        RB.211-72-C879 Revision                1,200
                                              inspect and            4, 3.A.(1) through
                                              relubricate, OR        3.A.(7), dated April 2,
                                                                     2004.
                             ..............  (ii) Wave Probe......  RB.211-72-C879 Revision                1,000
                                                                     4, 3.B.(1) through
                                                                     3.B.(7), dated April 2,
                                                                     2004.
(2) In Shop................          17,000  Root Probe, inspect    RB.211-72-C879 Revision                1,200
                                              and relubricate..      4, 3.C.(1) through
                                                                     3.C.(4), dated April 2,
                                                                     2004.
----------------------------------------------------------------------------------------------------------------

Optional Terminating Action

    (l) 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

    (m) 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

    (n) Previous credit is allowed for initial and repetitive 
inspections performed using AD 2003-12-15 (Amendment 39-13200, 68 FR 
37735, June 25, 2003) and RR MSB No. RB.211-72-C879, Revision 3, 
dated October 9, 2002.

Material Incorporated by Reference

    (o) You must use Rolls-Royce Mandatory Service Bulletin No. 
RB.211-72-C879, Revision 4, dated April 2, 2004, to perform the 
inspections and relubrication required by this AD. The Director of 
the Federal Register approved the incorporation by reference of this 
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. You can get a copy from Rolls-Royce plc, PO Box 31, Derby, 
England, DE248BJ; telephone: 011-44-1332-242-424; fax: 011-44-1332-
249-936. You may review copies at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or on the Internet at http://dms.dot.gov; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Related Information

    (p) CAA airworthiness directive AD 002-01-2000, dated October 9, 
2002, also addresses the subject of this AD.


[[Page 3867]]


    Issued in Burlington, Massachusetts, on January 18, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1384 Filed 1-26-05; 8:45 am]
BILLING CODE 4910-13-P