[Federal Register Volume 68, Number 124 (Friday, June 27, 2003)]
[Rules and Regulations]
[Pages 38171-38172]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-16283]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-10-AD; Amendment 39-13213; AD 2003-13-12]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-22B Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Rolls-Royce plc (RR) RB211-22B series turbofan engines 
with intermediate pressure (IP) compressor stage 6 to 7 rotor shaft 
assembly part number (P/N) UL37094 installed. This amendment requires 
removal from service of IP compressor stage 6 to 7 rotor shaft 
assemblies P/N UL37094 before reaching newly reduced life limits. This 
amendment is prompted by the discovery of corrosion during inspection 
and analysis of IP compressor stage 6 to 7 rotor shaft assemblies 
returned from the field. The actions specified by this AD are intended 
to prevent corrosion-induced cracking of the IP compressor stage 6 to 7 
rotor shaft assembly, resulting in an uncontained engine failure and 
damage to the airplane.

DATES: Effective August 1, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce plc, P.O. Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-245-418. This 
information may be examined, by appointment, at the Federal Aviation 
Administration (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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to RR RB211-22B series turbofan engines with IP compressor 
stage 6 to 7 rotor shaft assembly P/N UL37094 installed was published 
in the Federal Register on December 2, 2002 (67 FR 71495). That action 
proposed to require removal from service of IP compressor stage 6 to 7 
rotor shaft assemblies P/N UL37094 before reaching newly reduced life 
limits.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-13-12 Rolls-Royce plc: Amendment 39-13213. Docket No. 2002-NE-
10-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce (RR) RB211-22B series turbofan engines with 
intermediate pressure (IP) compressor stage 6 to 7 rotor shaft 
assembly part number (P/N) UL37094 installed. These engines are 
installed on, but not limited to Lockheed Martin L1011 airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not

[[Page 38172]]

been eliminated, the request should include specific proposed 
actions to address it.

    Compliance: Compliance with this AD is required as indicated, 
unless already done.
    To prevent corrosion-induced cracking of the IP compressor stage 
6 to 7 rotor shaft assembly, resulting in an uncontained engine 
failure and damage to the airplane, do the following:
    (a) For engines that have not incorporated RR service bulletin 
(SB) 72-8700, remove IP compressor stage 6 to 7 rotor shaft 
assemblies from service before accumulating 13,500 cycles-since-new 
(CSN).
    (b) For engines that have incorporated RR SB 72-8700, remove IP 
compressor stage 6 to 7 rotor shaft assemblies from service before 
accumulating 12,980 CSN.
    (c) After the effective date of this AD, do not install any IP 
compressor stage 6 to 7 rotor shaft assembly, P/N UL37094, that has 
accumulated the CSN specified in paragraph (a) or (b) of this AD.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Sec. Sec.  21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be done.

Effective Date

    (f) This amendment becomes effective on August 1, 2003.

    Issued in Burlington, Massachusetts, on June 23, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-16283 Filed 6-26-03; 8:45 am]
BILLING CODE 4910-13-P