[Federal Register Volume 68, Number 208 (Tuesday, October 28, 2003)]
[Rules and Regulations]
[Pages 61336-61338]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-26916]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-33-AD; Amendment 39-13351; AD 2003-22-04]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce plc (RR) RB211-524 series turbofan engines with certain 
part number (PN) and serial number (SN) low pressure (LP) compressor 
fan blades installed. This AD requires inspection of certain LP 
compressor fan blade roots and replacement or repair of blades if 
damage is not within acceptable limits. This AD is prompted by the 
discovery of damaged LP compressor fan blade roots resulting from 
entrapment of ceramic polishing media between the blade roots and the 
masking boot during blade root repair. We are issuing this AD to 
prevent possible uncontained multiple LP compressor fan blade release, 
and damage to the airplane.

DATES: Effective November 12, 2003. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of November 12, 2003.
    We must receive any comments on this AD by December 29, 2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    [sbull] By mail: The Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2003-NE-33-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected]
    You can get the service information referenced in this AD from 
Rolls-Royce plc, PO Box 31, Derby, England; telephone: International 
Access Code 011, Country Code 44, 1332-249428, fax International Access 
Code 011, Country Code 44, 1332-249223.
    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. You may examine the service 
information, by appointment, at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the FAA that an unsafe condition may exist on certain RR 
RB211-524 series turbofan engines. The CAA received

[[Page 61337]]

reports of LP compressor fan blade root damage due to entrapment of 
ceramic polishing media between the blade roots and masking boots while 
doing RR Repair Scheme FRS5712, subtask 72-31-11-380-119.

Relevant Service Information

    We have reviewed and approved the technical contents of Rolls-Royce 
plc Mandatory Service Bulletin (MSB) No. RB.211-72-D184, Revision 3, 
dated December 20, 2002, that provides procedures for inspection of 
blade roots of LP compressor fan blades that were repaired using RR 
Repair Scheme FRS5712, subtask 72-31-11-380-119, and replacement or 
repair of blades if damage is not within acceptable limits. The CAA 
classified this service bulletin as mandatory and issued AD 005-04-2001 
in order to ensure the airworthiness of these Rolls-Royce plc engines 
in the UK.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the 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 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

    Although no airplanes that are registered in the United States use 
these RR RB211-524 series turbofan engines, the possibility exists that 
these engine models could be used on airplanes that are registered in 
the United States in the future. The unsafe condition described 
previously is likely to exist or develop on other engines of the same 
type design. We are issuing this AD to prevent possible uncontained 
multiple LP compressor fan blade release, and damage to the airplane. 
This AD requires inspection of blade roots of LP compressor fan blades 
that were repaired using RR Repair Scheme FRS5712, subtask 72-31-11-
380-119, and replacement or repair of blades if damage is not within 
acceptable limits. The inspections are to be performed by following a 
compliance schedule based on engine model and cycles accumulated.
    You must use the service information described previously to 
perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. Therefore, a situation exists that allows the 
immediate adoption of this regulation.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

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. 2003-NE-33-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.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

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.

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. 2003-NE-33-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 adding the following new airworthiness 
directive:

2003-22-04 Rolls-Royce plc: Amendment 39-13351. Docket No. 2003-NE-
33-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
12, 2003.

Affected ADs

    (b) None.

[[Page 61338]]

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211-524G2-19,-
524G2-T-19, -524G3-19, -524G3-T-19, -524H2-19, -524H2-T-19, -524H-
36, and ``524-H-T-36 turbofan engines with low pressure (LP) 
compressor fan blades part numbers (PNs) and serial numbers (SNs) as 
listed in Table 1 of RR Mandatory Service Bulletin (MSB) No. RB.211-
72-D184, Revision 3, dated December 20, 2002, installed. These 
engines are installed on, but not limited to, Boeing 747 and 767 
series airplanes.

Unsafe Condition

    (d) This AD was prompted by the discovery of damaged LP 
compressor blade roots resulting from entrapment of ceramic 
polishing media between the blade roots and the masking boot during 
blade root repair. We are issuing this AD to prevent possible 
uncontained multiple LP compressor fan blade release, 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.

Reworked LP Compressor Fan Blades Not Affected

    (f) LP compressor fan blades listed in Table 1 of RR MSB No. 
RB.211-72-D184, Revision 3, dated December 20, 2002, that have been 
reworked using Service Bulletin (SB) No. RB.211-72-D051, dated 
August 23, 2000, or SB No. RB.211-72-D020, dated April 19, 2000, are 
considered to have had all damage addressed during rework and are 
not affected by this AD.

Removal and Inspection of LP Compressor Fan Blades

    (g) Using the compliance thresholds in Table 1 of this AD, 
remove LP compressor fan blades and inspect the blade roots of all 
LP compressor fan blades listed by PN and SN in Table 1 of RR MSB 
No. RB.211-72-D184, Revision 3, dated December 20, 2002. Follow the 
inspection criteria in paragraph 3.B. of the Accomplishment 
Instructions of RR MSB No. RB.211-72-D184, Revision 3, dated 
December 20, 2002.

   Table 1.--LP Compressor Fan Blade Inspection Compliance Thresholds
------------------------------------------------------------------------
           Engine models                    Compliance thresholds
------------------------------------------------------------------------
(1) RB211-524G2-19, -524G2-T-19, -   (i) For blades exceeding 2,000
 524G3-19, -524G3-T-19, -524H-36, -   cycles-since-incorporation of RR
 524H-T-36.                           Repair Scheme FRS5712, subtask 72-
                                      31-11-380-119, before further
                                      flight.
                                     (ii) For blades with fewer than
                                      2,000 cycles-since-incorporation
                                      of RR Repair Scheme FRS5712,
                                      subtask 72-31-11-380-119, before
                                      accumulating 2,000 cycles-since-
                                      incorporation of the Repair
                                      Scheme.
(2) RB211-524H-36 and RB211-524-H-T- Before further flight.
 36 Engines on Short Haul Operation
 Airplanes.
(3) RB211-524H2-19 and -524H2-T-19.  Before accumulating 800 cycles-
                                      since-incorporation of RR Repair
                                      Scheme FRS5712, subtask 72-31-11-
                                      380-119, or before December 2005,
                                      whichever occurs sooner.
(4) RB211-524H-36 and RB211-524-H-T- Before accumulating 870 cycles-
 36 Engines On Long Haul Operation    since-incorporation of RR Repair
 Airplanes.                           Scheme FRS5712, subtask 72-31-11-
                                      380-119, or before December 2005,
                                      whichever occurs sooner.
------------------------------------------------------------------------

Removal From Service or Repair of LP Compressor Fan Blades That Do Not 
Pass Inspection

    (h) Remove from service LP compressor fan blades that do not 
pass the inspection criteria in paragraph 3.B. of the Accomplishment 
Instructions of RR MSB No. RB.211-72-D184, Revision 3, dated 
December 20, 2002, or repair blades. Follow paragraph 3.B.(3)(b) of 
the Accomplishment Instructions of RR MSB No. RB.211-72-D184, 
Revision 3, dated December 20, 2002 to repair blades.

Prohibition of LP Compressor Fan Blades Not Inspected or Repaired

    (i) After the effective date of this AD, do not install any 
blade that was removed as specified in paragraph (g) of this AD, 
unless the blade has passed inspection or has been repaired using 
paragraph 3.B. of the Accomplishment Instructions of RR MSB No. 
RB.211-72-D184, Revision 3, dated December 20, 2002.

Definition

    (j) For the purpose of this AD, a Long Haul Operation is defined 
as an operation with an average stage length of more than five 
hours.

Alternative Methods of Compliance

    (k) 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.

Material Incorporated by Reference

    (l) You must use Rolls-Royce MSB No. RB.211-72-D184, Revision 3, 
dated December 20, 2002, to perform the blade inspection and repair 
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; telephone: 
International Access Code 011, Country Code 44, 1332-249428; fax 
International Access Code 011, Country Code 44, 1332-249223. You may 
review copies at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., Suite 
700, Washington, DC.

Related Information

    (m) CAA airworthiness directive 005-04-2001, dated April 20, 
2001, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on October 20, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-26916 Filed 10-27-03; 8:45 am]
BILLING CODE 4910-13-P