[Federal Register Volume 68, Number 147 (Thursday, July 31, 2003)]
[Proposed Rules]
[Pages 44902-44904]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-19482]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-13-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc (RR) RB211-22B, RB211-
524, and RB211-535 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: This notice revises an earlier proposed airworthiness 
directive (AD), applicable to (RR) RB211-535E4 series turbofan engines. 
That proposal would have required disassembling and inspecting all the 
engine mounts for cracks, refurbishing the engine mounts, and replacing 
the front mount thrust link spherical bearing. That proposal was 
prompted by reports of corrosion and fatigue cracks in the mount pins, 
the spherical bearings, and the support links and their respective 
spherical bearings. This action revises the proposed rule by expanding 
the applicability from RB211-535E4 series turbofan engines to include 
RB211-22B, RB211-524, and RB211-535 series turbofan engines, and by 
requiring the installation of a front engine mount housing and link 
support assembly that has a serialized, life limited spherical bearing 
installed. This action also revises the proposed rule by eliminating 
the requirements for disassembling and inspecting all the engine mounts 
for cracks, and refurbishing the engine mounts. The actions specified 
by this proposed AD are intended to prevent failure of the front engine 
mount housing and link support assembly due to cracks, that could 
result in loss of the engine.

DATES: Comments must be received by September 29, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-13-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

[[Page 44903]]

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, DE24 8BJ, United 
Kingdom; telephone 011-44-1332-242424; fax 011-44-1332-249936. 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: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7751; fax (781) 238-7199.

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 2001-NE-13-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. 2001-NE-13-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
RB211-535E4 series turbofan engines, was published as a notice of 
proposed rulemaking (NPRM) in the Federal Register on February 26, 2002 
(67 FR 8739). That NPRM would have required disassembling and 
inspecting all engine mounts for cracks, refurbishing the engine 
mounts, and replacing the front mount thrust link spherical bearing. 
That NPRM was prompted by reports of corrosion and fatigue cracks in 
the mount pins, the spherical bearings, and the support links and their 
respective spherical bearings. That condition, if not corrected, could 
result in failure of the engine mounts due to cracks that could result 
in loss of an engine.
    Since that NPRM was issued, the FAA has become aware that the Civil 
Aviation Authority (CAA), which is the aviation authority for the U.K., 
has cancelled AD 004-08-2000, which addresses the subject of the NPRM, 
and that RR has downgraded the category of Service Bulletin (SB) 
RB.211-71-5291, Revision 14, dated March 13, 2001, which required 
compliance of that SB in the NPRM, to recommended. RR has since issued 
a mandatory SB RB.211-71-D437, Revision 1, dated February 28, 2003, 
which introduces a serialized, life-limited, spherical bearing for the 
engine front mount housing and link support assembly and introduced the 
inspection requirements of the engine front and rear mounts in the Time 
Limit Manual. Therefore, the compliance with the requirements of the SB 
RB.211-71-5291 is no longer required.
    The CAA has also issued AD 005-04-2002, dated April 2002, to 
mandate compliance with the new requirements as per the RR Service 
Bulletin (SB) RB.211-71-D437, Revision 1, dated February 28, 2003.
    Since this change expands the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of RR SB 
RB.211-71-D437, Revision 1, dated February 28, 2003, that introduces 
new production engine front mount housing and link support assemblies 
and describes procedures for reworking existing engine front mount 
housing and link support assemblies by installing a new serialized 
bearing.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on RR RB211-22B, RB211-524, and RB211-535 series 
turbofan engines installed on U.S. registered aircraft, the proposed AD 
would require the installation of a front engine mount housing and link 
support assembly that has a serialized, life limited spherical bearing 
installed, by either installing a new assembly or reworking the 
existing assembly. The actions must be done at the next Module 04 shop 
visit after the effective date of the AD but no later than April 1, 
2011, in accordance with the MSB described previously.

Economic Analysis

    There are approximately 2,214 RR RB211-22B, RB211-524, and RB211-
535 series turbofan engines of the affected design in the worldwide 
fleet. The FAA estimates that about 620 RB211-535 engines, and about 45 
RB211-524 and RB211-22B engines installed on airplanes of U.S. 
registry, would be affected by this proposed AD. The FAA also estimates 
that no additional labor costs would be incurred to perform the 
proposed actions. The FAA anticipates that the new hardware will be 
installed while the module is inducted into the shop for routine 
maintenance inspection before the compliance expiration date of this 
AD. The cost of a new serialized spherical bearing is approximately 
$592 for RB211-535 engines, $895 for RB211-524 engines, and $1,990 for 
RB211-22B engines. Based on these figures, the total cost of the 
proposed AD to U.S. operators is estimated to be $493,975.

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

[[Page 44904]]

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 adding the following new 
airworthiness directive:

Rolls-Royce plc: Docket No. 2001-NE-13-AD.

    Applicability This airworthiness directive (AD) is applicable to 
Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series 
turbofan engines. These engines are installed on, but not limited to 
Boeing 747, 757, 767, Lockheed L-1011, and Tupolev Tu204-120 
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 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 failure of the front engine mount due to cracks, that 
could result in loss of the engine, do the following at the next 
Module 04 shop visit after the effective date of this AD, but no 
later than April 1, 2011:
    (a) Replace existing engine front mount housing and link support 
assembly listed in Table 1 of this AD with new production part 
number (P/N) front mount housing and link support assembly, or with 
a reworked assembly, in accordance with paragraph 3 of 
Accomplishment Instructions of Mandatory Service Bulletin (MSB) No. 
RB211-71-D437, Revision 1, dated February 28, 2003. Table 1 follows:

  Table 1.--Front Mount Housing and Link Support Assembly Existing P/Ns
                            and Reworked P/Ns
------------------------------------------------------------------------
                                              New production or reworked
                Existing P/N                             P/N
------------------------------------------------------------------------
LK83038....................................  FW18695
LK83047....................................  FW18686
LK83057....................................  FW18691
LK83072....................................  FW18696
LK83110....................................  FW18697
LK83114....................................  FW18698
UL10472....................................  FW18694
UL25694....................................  FW18688
UL27054....................................  FW18687
UL27601....................................  FW18693
UL27612....................................  FW18689
UL27613....................................  FW18684
------------------------------------------------------------------------

    (b) Mark the Modules 04 after the rework with new P/N as 
specified in the following Table 2:

                      Table 2.--Module 04 Reworked
                                   P/N
------------------------------------------------------------------------
                Existing P/N                         Reworked P/N
------------------------------------------------------------------------
MO7127.....................................  MO7159
MO7130.....................................  MO7156
MO7133.....................................  MO7153
MO7134.....................................  MO7152
MO7135.....................................  MO7154
MO7149.....................................  MO7158
MO7150.....................................  MO7155
MO7151.....................................  MO7157
MO7202.....................................  MO7214
MO7206.....................................  MO7216
MO7207.....................................  MO7215
MO7208.....................................  MO7213
------------------------------------------------------------------------

    (c) Information on engine front mount housing and link support 
assembly disassembly, inspection, replacement of the time limited 
spherical bearing, and reassembly, can be found in RR Engine Manual, 
section 71-21-01.

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 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 005-04-2002, dated April 2002.


    Issued in Burlington, Massachusetts, on July 24, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-19482 Filed 7-30-03; 8:45 am]
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