[Federal Register Volume 67, Number 38 (Tuesday, February 26, 2002)]
[Proposed Rules]
[Pages 8739-8741]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-4367]


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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) RB211-535E4 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 adopt a 
new airworthiness directive (AD) that is applicable to RR RB211-535E4 
series turbofan engines. This proposal would require disassembling and 
inspecting all engine mounts for cracks, refurbishing the engine 
mounts, and replacing the front mount thrust link spherical bearing. 
This proposal is prompted by reports of corrosion and fatigue cracks in 
the mount pins, the spherical bearings, and the support links and their 
respective spherical bearings. The actions specified by the proposed AD 
are intended to prevent failure of the engine mounts due to cracks that 
could result in loss of an engine.

DATES: Comments must be received by April 29, 2002.

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 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.

FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7744, 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

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for

[[Page 8740]]

the United Kingdom (UK), recently notified the FAA that an unsafe 
condition may exist on RR RB211-535E4 series turbofan engines. The CAA 
advises that there have been reports of stress and fatigue cracks found 
in engine mount assemblies, part numbers (P/N's) B71210101 (front) and 
B71210201 (rear). There were two instances of rear mount pin cracking, 
two instances of front mount spherical bearing cracking, corrosion of 
the rear mount support links and their respective spherical bearings, 
and a number of instances of cracking in the center spherical bearing 
of the front mount thrust link. Because this condition could cause 
failure of the engine mounts due to cracks that could result in loss of 
an engine, the CAA considers it necessary to make disassembly and 
inspection of these engine mounts mandatory. The CAA has issued AD 004-
08-2000, dated March 31, 2001, in order to assure the airworthiness of 
these Rolls-Royce engines in the UK.

Bilateral Agreement Information

    This engine model is manufactured in the UK, and is 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 RR RB211-535E4 series turbofan engines of the 
same type design that are used on airplanes registered in the United 
States, the proposed AD would require complete disassembling of the 
engine mounts, P/N's B71201101 and B71210201, inspecting for cracks, 
refurbishing the engine mounts, and replacing the front mount thrust 
link spherical bearing. These actions would be required to be done 
before accumulating 12,000 cycles-since-new (CSN) or 36,000 engine-
hours-since-new (EHSN), whichever is earlier, if engine cycles at next 
shop visit exceeds 5,000 cycles, and thereafter within every 12,000 
cycles-since-last-compliance or 36,000 hours-since-last-compliance, 
whichever is earlier. For engines with greater than 12,000 CSN or 
36,000 EHSN, these actions would be required to be done within 500 
cycles-in-service, or 1,500 engine-hours-in-service, whichever is 
earlier.

Economic Analysis

    There are approximately 1,128 engines of the affected design in the 
worldwide fleet. The FAA estimates that 500 engines installed on 
airplanes of U.S. registry would be affected by this proposed AD. The 
FAA also estimates that it would take approximately 32 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 $491 
per engine. Based on these figures, the total cost impact of the 
proposed AD on U.S. operators is estimated to be $1,205,500.

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 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) Model RB211-535E4-37, -535E4-B-37 and -
535E4-B-75 turbofan engines with engine mount assemblies, part 
numbers (P/N's) B71210101 and B71210201, installed. These engines 
are installed on, but not limited to Boeing 757 series 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 (c) 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 engine mounts due to cracks that could 
result in loss of an engine, do the following:

Inspection of Engine Mounts for Cracks

    (a) Using the compliance times specified in the following Table, 
do the following actions:

[[Page 8741]]



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  Number of Cycles-Since-New
 (CSN) or Engine-Hours-Since-
  New (EHSN) on the effective             Initial compliance           Repetitive compliance by the earlier of--
        date of this AD
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(1) Fewer than 5,000 CSN......  At the next shop visit after           (i) 12,000 cycles-since-last-compliance
                                 accumulating 5,000 CSN, but not to     (CSLC), or
                                 exceed 12,000 CSN or 36,000 EHSN.     (ii) 36,000 engine-hours-since-last-
                                                                        compliance (EHSLC).
(2) 5,000 to 12,000 CSN or      At the next shop visit, but not to     (i) 12,000 CSLC, or
 12,000 to 36,000 EHSN.          exceed 12,000 CSN or 36,000 EHSN.     (ii) 36,000 EHSLC.
----------------------------------------------------------------------------------------------------------------
(3) Greater than 12,000 CSN or  Within 500 cycles-in-service or 1,500  (i) 12,000 CSLC, or
 36,000 EHSN.                    engine hours-in-service, whichever    (ii) 36,000 EHSLC.
                                 is earlier, after the effective date
                                 of the AD.
----------------------------------------------------------------------------------------------------------------

    (4) Disassemble front engine mounts, P/N 71210101, and rear 
engine mounts, P/N 71210201. Procedures for disassembly and 
inspection/check of the engine mounts can be found in sections 71-
21-01 and 71-21-02 of the engine manual (EM).
    (5) Inspect for cracks using the Fluorescent Penetrant or 
Magnetic Particle inspection methods.
    (6) Assemble the engine mounts, insuring application of OMat 4/
23 Neverseez. Procedures for assembling the engine mounts can be 
found in sections 71-21-01 and 71-21-02 of the EM.

Credit for Previous Compliance

    (b) Compliance with RR Service Bulletin (SB) RB.211-71-5291 
constitutes compliance with the initial compliance requirements or 
repetitive compliance requirements specified in paragraph (a) of 
this AD.

Alternative Methods of Compliance

    (c) 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

    (d) Special flight permits may be issued in accordance 
Secs. 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 004-08-2000, dated March 13, 2001, and in RR SB No. 
RB.211-71-5291, Revision 14, dated March 13, 2001.


    Issued in Burlington, Massachusetts, on February 19, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-4367 Filed 2-25-02; 8:45 am]
BILLING CODE 4910-13-P