[Federal Register Volume 69, Number 35 (Monday, February 23, 2004)]
[Rules and Regulations]
[Pages 8101-8103]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3681]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-29-AD; Amendment 39-13486; AD 2004-04-05]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company) AE 3007 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 Corporation (RR) (formerly Allison Engine Company) 
AE 3007A, AE 3007A1/1, AE 3007A1/2, AE 3007A1, AE 3007A1/3, AE 3007A1P, 
and AE 3007A3 turbofan engines. That AD currently requires initial and 
repetitive inspections for bearing material contamination of the engine 
oil system. This AD requires the same inspections but with an extended 
repetitive inspection interval, and adds terminating actions to the 
repetitive inspections required by this AD. This AD is prompted by 
design changes introduced by the manufacturer that reduce the axial 
load on the No. 1 bearing. We are issuing this AD to prevent the rapid 
failure of the No. 1 bearing, which could result in smoke in the cabin 
and an uncommanded in-flight engine shutdown.

DATES: Effective March 9, 2004. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of March 9, 2004.
    We must receive any comments on this AD by April 23, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     By mail: The Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-29-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 Corporation, P.O. Box 420, Indianapolis, IN 46206-0420; 
telephone (317) 230-3030.
    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; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018; telephone: (847) 294-
7836; fax: (847) 294-7834.

SUPPLEMENTARY INFORMATION: On April 16, 2001, we issued AD 2001-08-15, 
Amendment 39-12192 (66 FR 21067, April 27, 2001). That AD requires 
initial and repetitive inspections for bearing material contamination 
of the engine oil system. That AD was prompted by reports of rapid 
failures of the No. 1 bearing. That AD also allows as terminating 
action to the repetitive inspections, incorporation of Embraer Service 
Bulletin (SB) 145-79-0001, dated April 24, 1998. That SB installs an 
electrical jumper in an airplane electrical connector, which adds a 
second function to the Oil Impending Bypass advisory message, on the 
Engine Indication and Crew Alerting System (EICAS). After incorporation 
of the SB, this message can either represent that there is an oil 
impending bypass, or that the magnetic chip detector plug has collected 
enough ferrous metal to indicate possible initiation of bearing 
failure. That condition, if not corrected, could result in smoke in the 
cabin and an uncommanded in-flight engine shutdown.

Actions Since AD 2001-08-15 Was Issued

    Since that AD was issued, the manufacturer has introduced several 
turbine design changes, each of which sufficiently reduces the axial 
load on the No. 1 bearing, to virtually eliminate the potentially 
unsafe condition of rapid, undetected bearing failure. The design 
changes include:
     Modifying the current high pressure (HP)-to-low 
pressure (LP) seal assembly, part number (P/N) 23068183, with a large 
geometric rear seal diameter, and remarking it to new P/N 23073953. 
This modified seal assembly adjusts interstage turbine cavity pressure 
and effectively reduces the axial load on the No. 1 bearing.
     Introducing new HP-to-LP seal assemblies, P/Ns 
23074463, 23074729, 23076526, and 23077397, with a smaller geometric 
rear seal diameter. These new seal assemblies also reduce the axial 
load on the No. 1 bearing.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following RR service bulletins (SBs) and Embraer SB:
     RR SB AE 3007A-79-034, dated May 14, 2002, which 
provides procedures for inspecting for bearing material contamination 
of the engine oil system by reviewing the maintenance page on the 
cockpit Multi Function Display.
     RR SB AE 3007A-72-199, Revision 3, dated May 13, 
2002, which provides procedures to modify the HP-to-LP seal assembly, 
P/N 23068183, and remark seal assembly to P/N 23073953.
     RR SB AE 3007A-72-213, Revision 1, dated May 13, 
2002, which provides procedures to install new design HP-to-LP seal 
assembly, P/N 23074729.
     RR SB AE 3007A-72-213, Revision 2, dated 
November 20, 2003, which provides procedures to install new design HP-
to-LP seal assembly, P/N 23077397.
     RR SB AE 3007A-72-248, dated July 29, 2003, 
which provides procedures to install new design HP-to-LP seal assembly, 
P/N 23074463.
     RR SB AE 3007A-72-263, Revision 1, dated March 
4, 2003, which provides procedures to modify the HP-to-LP seal 
assembly, P/N 23074729, and remark seal assembly to P/N 23076526.
     RR SB AE 3007A-72-284, dated October 16, 2003, 
which provides procedures to modify the HP-to-LP seal assembly, P/N 
23074729 or P/N 23076526, and remark seal assembly to P/N 23077397.
     Embraer SB 145-79-0001, dated April 24, 1998, 
which provides procedures to modify the airplane wiring so that the oil 
impending bypass message will be displayed in the cockpit when the 
primary engine magnetic chip detector captures debris.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other RR AE 3007A, AE 3007A1/1, AE 3007A1/2, AE 3007A1, AE 
3007A1/3, AE 3007A1P, and AE 3007A3 turbofan engines of the same type 
design. We are issuing this AD to prevent the rapid failure of the No. 
1 bearing, which could result in smoke in the cabin and an uncommanded 
in-flight engine shutdown. This AD requires initial and repetitive 
inspections for bearing material contamination of the engine oil 
system, and adds terminating actions to the repetitive inspections 
required by this AD. Six of the seven terminating actions listed, 
eliminate the unsafe condition by

[[Page 8102]]

installing new or reworked parts, and one terminating action eliminates 
the unsafe condition by installing an electrical jumper in an airplane 
electrical connector, which adds a second function to the Oil Impending 
Bypass advisory message, on the EICAS. You must do these actions in 
accordance with the service information described previously.

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 impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

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. 2000-NE-29-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 through 
a nonwritten communication, 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 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. 2000-NE-29-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:

2004-04-05 Rolls-Royce Corporation: Amendment 39-13486. Docket No. 
2000-NE-29-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 9, 
2004.

Affected ADs

    (b) This AD supersedes AD 2001-08-15, Amendment 39-12192.

Applicability

    (c) This AD is applicable to Rolls-Royce Corporation (RR) 
(formerly Allison Engine Company) AE 3007A, AE 3007A1/1, AE 3007A1/
2, AE 3007A1, AE 3007A1/3, AE 3007A1P, and AE 3007A3 turbofan 
engines. These engines are installed on, but not limited to, Embraer 
Model EMB-145, EMB-145ER, EMB-145MR, EMB-145LR, EMB-135ER, and EMB-
135LR airplanes.

Unsafe Condition

    (d) This AD is prompted by design changes introduced by the 
manufacturer that reduce the No. 1 bearing load. The actions 
specified in this AD are intended to prevent the rapid failure of 
the No. 1 bearing, which could result in smoke in the cabin and an 
uncommanded in-flight engine shutdown.

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.

Inspection for Bearing Material Contamination of the Oil System

    (f) Inspect for bearing material contamination of the oil system 
using paragraph 2.A. of the Accomplishment Instructions of RR 
service bulletin (SB) No. AE 3007A-79-034, dated May 14, 2002, as 
follows:
    (1) Initially inspect within 50 flight hours or five flight days 
after the effective date of this AD.
    (2) Thereafter, inspect every 50 flight hours or every five 
flight days.

Terminating Actions

    (g) As terminating actions to the repetitive inspections 
specified in paragraph (f)(2) of this AD, do any one of the 
following paragraphs (g)(1) through (g)(7), by December 31, 2007:
    (1) Modify high pressure (HP)-to-low pressure (LP) seal 
assembly, part number (P/N) 23068183, and remark to P/N 23073953, at 
engine overhaul, using RR SB AE 3007A-72-199, Revision 3, dated May 
13, 2002.
    (2) Install new design HP-to-LP seal assembly, P/N 23074729, at 
engine overhaul, using RR SB AE 3007A-72-213, Revision 1, dated May 
13, 2002.
    (3) Install new design HP-to-LP seal assembly, P/N 23077397, at 
engine overhaul, using RR SB AE 3007A-72-213, Revision 2, dated 
November 20, 2003.
    (4) Install new design HP-to-LP seal assembly, P/N 23074463, at 
engine overhaul, using RR SB AE 3007A-72-248, dated July 29, 2003.
    (5) Modify HP-to-LP seal assembly, P/N 23074729, and remark to 
P/N 23076526,

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at engine overhaul, using RR SB AE 3007A-72-263, Revision 1, dated 
March 4, 2003.
    (6) Modify HP-to-LP seal assembly, P/N 23074729 or P/N 23076526, 
and remark to P/N 23077397, at engine overhaul, using RR SB AE 
3007A-72-284, dated October 16, 2003.
    (7) Using Embraer SB 145-79-0001, dated April 24, 1998, modify 
the airplane wiring so that the oil impending bypass message will be 
displayed in the cockpit when the primary engine magnetic chip 
detector captures debris.

Alternative Methods of Compliance

    (h) The Manager, Chicago Aircraft 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

    (i) The Director of the Federal Register approved the 
incorporation by reference of the Rolls-Royce (RR) documents and 
Embraer document listed in Table 1 of this AD in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. You may get RR copies from Rolls-
Royce Corporation, P.O. Box 420, Indianapolis, IN 46206-0420; 
telephone (317) 230-3030, and Embraer copies from Emprasa Brasiliera 
de Aeronautica S.A. (EMBRAER), P.O. Box 343-CEP 12.225, Sao Jose dos 
Campos-SP, Brazil. 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. Table 1 
follows:

                                      Table 1.--Incorporation by Reference
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                                Page number(s) shown on    Revision level shown on
       Service bulletin                 the page                   the page             Date shown on the page
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RR SB AE 3007A-79-034........  All......................  Original.................  May 14, 2002.
RR SB AE 3007A-72-199........  All......................  3........................  May 13, 2002.
RR SB AE 3007A-72-213........  All......................  1........................  May 13, 2002.
RR SB AE 3007A-72-213........  All......................  2........................  November 20, 2003.
RR SB AE 3007A-72-248........  All......................  Original.................  July 29, 2003.
RR SB AE 3007A-72-263........  All......................  1........................  March 4, 2003.
RR SB AE 3007A-72-284........  All......................  Original.................  October 16, 2003.
Embraer SB-145-79-0001.......  All......................  Original.................  April 24, 1998.
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Related Information

    (j) None.

    Issued in Burlington, Massachusetts, on February 13, 2004.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-3681 Filed 2-20-04; 8:45 am]
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