[Federal Register Volume 68, Number 47 (Tuesday, March 11, 2003)]
[Proposed Rules]
[Pages 11476-11479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-5582]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-369-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Models L-1011 Airplanes 
and Rolls-Royce plc RB211 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to 
supersede an existing airworthiness directive (AD) that is applicable 
to Lockheed Martin L-1011-385 series airplanes. That AD currently 
requires modifications of the engine turbine cooling air panel at the 
flight engineer/second officer's console, pilot's caution and warning 
light panel on the main instrument panel, and installation of an engine 
turbine air temperature monitoring system. This proposal would require 
the same modifications. In addition, this proposal would add Lockheed 
Martin L-1011-385 series airplanes with RB211-22B-02 series engines to 
the applicability, would require installation of a revised engine front 
bearing housing assembly, installation of a revised speed probe loom 
electrical support assembly, and installation of a low pressure (LP) 
compressor shaft extreme axial movement detector system. Also, this 
proposal would require additional modifications to the engine turbine 
cooling air panel at the flight engineer/second officer's console, 
pilot's caution and warning light panel on the main instrument panel. 
This proposal is prompted by reports of an undetected fire breaching 
the high speed gearbox (HSGB) case on certain Rolls-Royce engines 
installed on in-service airplanes due to lack of an internal fire 
detection system within the HSGB. In addition, this proposal is 
prompted by an undetected LP compressor shaft location

[[Page 11477]]

bearing failure, and the discovery of possible fatigue failure of the 
speed probe loom electrical support assembly. The actions specified by 
the proposed AD are intended to prevent undetected fires originating 
within the HSGB from breaching the HSGB case, which could result in 
engine damage and increased difficulty in extinguishing a fire, and to 
prevent undetected LP compressor shaft location bearing failure, which 
could result in LP compressor and turbine shaft assembly failure, 
turbine overspeed, and possible uncontained engine failure.

DATES: Comments must be received by May 12, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NM-369-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in the proposed rule may be 
obtained from Rolls-Royce plc, P.O. Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242-424; fax: 011-44-1332-245-418 and Lockheed 
Martin & Logistics Center, 120 Orion Street, Greenville, South Carolina 
29605. This information may be examined, by appointment, at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

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, and Robert A. Bosak, Aerospace Engineer, 
Atlanta Aircraft Certification Office, One Crown Center, Suite 475, 
1895 Phoenix Blvd., Atlanta, GA 39348, telephone: (770) 703-6094, fax: 
(770) 703-6097.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-369-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2000-NM-369-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    On August 15, 2001, the FAA issued airworthiness directive (AD) 
2000-17-10 R1, Amendment 39-12378 (66 FR 44030 August 22, 2001), to 
require modifications of the engine turbine cooling air panel at the 
flight engineer/second officer's console, pilot's caution and warning 
light panel on the main instrument panel, and installation of an engine 
turbine air temperature monitoring system. That action was prompted by 
reports of an undetected fire breaching the HSGB case on certain Rolls-
Royce engines installed on in-service airplanes due to lack of an 
internal fire detection system within the HSGB. That condition, if not 
corrected, could result in engine damage and increased difficulty in 
extinguishing a fire.
    Since that AD was issued, it has been determined that Lockheed 
Martin L-1011-385 series airplanes with RB211-22B-02 series engines 
need to be added to the applicability. Also since that AD was issued, 
the Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom (U.K.), notified the FAA that other 
unsafe conditions may exist on Rolls-Royce plc RB211-22B-02, RB211-
524B-02, RB211-524B-B-02, RB211-524B3-02, RB211-524B4-02, and RB211-
524B4-D-02 series turbofan engines which are installed in Lockheed 
Martin models L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-
1011-385-3 airplanes. The CAA has reported that recently an event 
occurred in which the continued operation of an engine with an 
undetected failure of the LP compressor shaft location bearing, 
resulted in failure of the LP compressor and turbine shaft assembly and 
severe secondary engine damage. The manufacturer states that the method 
used to detect pending failure of the LP compressor shaft location 
bearing is to monitor the LP vibration level on an indicator in the 
cockpit. This method has proved ineffective.
    This proposal contains actions that would be required for these 
Rolls-Royce engines and the airplanes on which the engines are 
installed. Those actions must be done so that the installation of the 
engine turbine air temperature monitoring system and installation of 
the LP compressor shaft extreme axial movement detector system are 
complete. Without complete monitor and detector systems, engine damage 
and increased difficulty in extinguishing a fire could occur, and 
failures of the LP compressor shaft location bearing would continue 
undetected. These actions have been coordinated with the Atlanta 
Aircraft Certification Office and the Transport Airplane Directorate. 
All parties agree that a single AD addressing these unsafe conditions 
and the complete modifications to address these unsafe conditions 
should be issued from the Engine and Propeller Directorate.

Manufacturer's Service Information

    Rolls-Royce plc has issued Mandatory Service Bulletins (MSB) 
RB.211-72-C863, dated February 15, 2002, applicable to RB211-22B-02 
engines and MSB RB.211-72-C963, dated December 4, 2001, applicable to 
RB211-524B-02, RB211-524B-B-02, RB211-524B3-02, RB211-524B4-02, and 
RB211-524B4-D-02 engines, that specify installation of an LP compressor 
shaft extreme axial movement detector system. These MSB's require 
compliance with five other service bulletins (SB's) concurrently or 
before accomplishing the applicable MSB. This proposal would require 
compliance with the latest revisions of these SB's, as listed in this 
proposal. The SB's are as follows:
    [sbull] RR SB RB.211-72-6149, Revision 9, dated November 24, 1999, 
which introduces a new design engine front

[[Page 11478]]

bearing housing assembly containing changes to the intermediate 
pressure (IP) and LP speed probe terminal block positions to prevent 
oil leakage.
    [sbull] RR SB RB.211-72-C178, Revision 1, dated March 9, 2001, 
which introduces a revised engine gearbox breather duct assembly that 
provides mounting locations for overheat detectors.
    [sbull] RR SB RB.211-77-C144, Revision 1, dated February 13, 2002, 
which introduces overheat detectors mounted in the engine gearbox 
breather duct assembly, to provide detection of temperature increase in 
the gearbox breather air flow, and early detection of fires originating 
in the gearbox.
    [sbull] RR MSB RB.211-71-E047, dated August 2, 2002, which 
introduces a revised speed probe loom electrical support assembly, 
located on the engine front bearing housing assembly.
    [sbull] Lockheed Martin SB 093-77-059, Revision 2, dated April 11, 
2002, which introduces modifications to the airplane instrument panels 
and consoles, necessary for compatibility with the installation of the 
engine turbine air temperature monitoring system.
    [sbull] Lockheed Martin SB 093-77-060, dated April 11, 2002, which 
introduces modifications to the airplane instrument panels and 
consoles, necessary for compatibility with the installation of engine 
failure indicators and LP compressor shaft extreme axial movement 
detector indicators.
    These modifications would be mandated by this proposal. The CAA 
classified MSB RB.211-72-C863, MSB RB.211-72-C963, and MSB RB.211-71-
E047 as mandatory and issued AD 006-02-2002, dated February 15, 2002, 
AD 006-12-2001, dated December 4, 2001, and AD 003-08-2002, dated 
August 2, 2002 respectively, in order to assure the airworthiness of 
these engines in the U.K.

Differences Between This AD and the Manufacturer's Service Information

    Although Mandatory Service Bulletins RB.211-72-C863 and RB.211-72-
C963 specify a fixed date for compliance for RB211-22B-02, RB211-524B-
02, RB211-524B-B-02, RB211-524B3-02, RB211-524B4-02 and RB211-524B4-D-
02 engines, the FAA requires the compliance to be done within a 
specified time span such as months or years from the effective date of 
the AD.

Bilateral Agreement Information

    These engine models are manufactured in the U.K. and are type 
certificated for operation in the United States under the provisions of 
Sec.  21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the CAA has kept the FAA informed of 
the situation described above. The FAA has 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.

Proposed Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Lockheed Martin models L-1011-385-1, L-1011-
385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes and Rolls-Royce 
plc RB211-22B-02, RB211-524B-02, RB211-524B-B-02, RB211-524B3-02, 
RB211-524B4-02, and RB211-524B4-D-02 series turbofan engines of the 
same type design that are used on airplanes registered in the United 
States, the proposed AD would require:
    [sbull] Modifications of the engine turbine cooling air panel at 
the flight engineer/second officer's console, pilot's caution and 
warning light panel on the main instrument panel.
    [sbull] Installation of an engine turbine air temperature 
monitoring system.
    [sbull] Installation of a revised engine front bearing housing 
assembly.
    [sbull] Installation of speed probe loom electrical support 
assembly part number (P/N) FW15212, if applicable.
    [sbull] Installation of an LP compressor shaft extreme axial 
movement detector system.
    The actions would be required to be done in accordance with the 
MSB's and SB's described previously.

Economic Analysis

    There are approximately 492 engines and 164 airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 270 
engines installed on 90 airplanes of U.S. registry would be affected by 
this proposed AD. The FAA estimates that it would take approximately 40 
work hours per engine to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $58,956 per engine. The FAA estimates that it would cost 
approximately $37,920 per airplane to do the airframe panel 
modifications. In addition, one airplane of U.S. registry would require 
speed probe loom electrical support assemblies P/N FW15212 installed on 
all three engines, at an estimated cost of $588 per engine. Based on 
these figures, the total cost of the proposed AD to U.S. operators is 
estimated to be $19,980,684.

Regulatory Analysis

    This proposed 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 proposed rule.
    For the reasons discussed above, I certify that this proposed 
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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-12378, 66 FR 
44030 August 22, 2001), and by adding a new airworthiness directive:

Lockheed Martin and Rolls-Royce plc: Docket No. 2000-NM-369-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Lockheed Martin models L-1011-385-1, L-1011-385-1-14, L-1011-385-
1-15, and L-1011-385-3 airplanes and Rolls-Royce plc (RR) RB211-22B-
02, RB211-524B-02, RB211-524B-B-02, RB211-524B3-02, RB211-524B4-02, 
and RB211-524B4-D-02 series turbofan engines.

    Note 1: This airworthiness directive (AD) applies to each 
airplane and engine identified in the preceding applicability

[[Page 11479]]

provision, regardless of whether it has been modified, altered, or 
repaired in the area subject to the requirements of this AD. For 
airplanes and 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 (e) 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 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 undetected fires originating within the high speed 
gearbox (HSGB) from breaching the HSGB case, which could result in 
engine damage and increased difficulty in extinguishing a fire, and 
to prevent undetected low pressure (LP) compressor shaft location 
bearing failure, which could result in LP compressor and turbine 
shaft assembly failure, turbine overspeed, and possible uncontained 
engine failure, do the following:

Requirements for All Applicable Airplanes and Engines

    (a) Incorporate the following service bulletins concurrently or 
before accomplishing the requirements of RR Mandatory Service 
Bulletin (MSB) RB.211-72-C963, dated December 4, 2001, or RR MSB 
RB.211-72-C863, dated February 15, 2002, whichever is applicable, as 
specified in paragraphs (b) through (d) of this AD:
    (1) Install a new design engine front bearing housing assembly 
in accordance with RR SB RB.211-72-6149, Revision 9, dated November 
24, 1999.
    (2) Modify airplane instrument panels and consoles, necessary 
for compatibility with the installation of the engine turbine air 
temperature monitoring system, in accordance with Lockheed Martin SB 
093-77-059, Revision 2, dated April 11, 2002.
    (3) Install a revised gearbox breather assembly in accordance 
with RR SB RB.211-72-C178, Revision 1, dated March 9, 2001.
    (4) Install overheat detectors in the gearbox breather duct 
assembly, in accordance with RR SB RB.211-77-C144, Revision 1, dated 
February 13, 2002.
    (5) Modify airplane instrument panels and consoles and install 
engine failure indicators and LP compressor shaft extreme axial 
movement detector indicators, in accordance with Lockheed Martin SB 
093-77-060, dated April 11, 2002.

RB211-524B-02 and RB211-524B-B-02 Engines

    (b) Within three months after the effective date of this AD, for 
RB211-524B-02 and RB211-524B-B-02 engines, do the following:
    (1) Install an LP compressor shaft extreme axial movement 
detector system in accordance with RR Mandatory Service Bulletin 
(MSB) RB.211-72-C963, dated December 4, 2001.
    (2) Replace existing speed probe loom electrical support 
assembly, located on the engine front bearing housing assembly, with 
speed probe loom electrical support assembly P/N FW15212, in 
accordance with 3.A. Accomplishment Instructions of RR MSB RB.211-
71-E047, dated August 2, 2002.

RB211-22B-02 Engines

    (c) Within three years after the effective date of this AD, for 
RB211-22B-02 engines, install an LP compressor shaft extreme axial 
movement detector system in accordance with RR MSB RB.211-72-C863, 
dated February 15, 2002.

RB211-524B3-02, RB211-524B4-02, and RB211-524B4-D-02 Engines

    (d) Within four years after the effective date of this AD, for 
RB211-524B3-02, RB211-524B4-02, and RB211-524B4-D-02 engines, 
install an LP compressor shaft extreme axial movement detector 
system in accordance with RR MSB RB.211-72-C963, dated December 4, 
2001.

Alternative Methods of Compliance

    (e) 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) 
for engines or Manager, Atlanta Aircraft Certification Office (ACO) 
for airplanes. Operators must submit their request through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, ECO, or Manager, ACO.

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

Special Flight Permits

    (f) 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 airplane to a location where 
the requirements of this AD can be done.

    Note 3: The subject of this AD is addressed in CAA airworthiness 
directive AD 006-12-2001, AD 003-08-2002, and AD 006-02-2002.


    Issued in Burlington, Massachusetts, on March 4, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-5582 Filed 3-10-03; 8:45 am]
BILLING CODE 4910-13-P