[Federal Register Volume 67, Number 85 (Thursday, May 2, 2002)]
[Rules and Regulations]
[Pages 21979-21981]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-10549]



[[Page 21979]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-36-AD; Amendment 39-12735; AD 2002-09-02]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc. Tay Model 650-15 and 
651-54 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) Tay model 650-15 and 651-54 
turbofan engines. This amendment requires revisions to the 
Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness (ICA) in the Time Limits Section of the Engine 
Manual for Rolls-Royce plc. Tay model 650-15 and 651-54 series turbofan 
engines to include required enhanced inspection of selected critical 
life-limited parts at each piece-part exposure. The actions specified 
by this AD are intended to prevent critical life-limited rotating 
engine part failure, which could result in an uncontained engine 
failure and damage to the airplane.

DATES: Effective date June 6, 2002.

ADDRESSES: The information referenced in this AD 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Rolls-Royce plc. (RR) Tay model 650-15 and 651-54 
turbofan engines was published in the Federal Register on December 4, 
2001 (66 FR 63009). That action proposed to require revisions to the 
Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness (ICA) in the Time Limits Section of the Engine 
Manual for RR Tay model 650-15 and 651-54 series turbofan engines to 
include required enhanced inspection of selected critical life-limited 
parts at each piece-part exposure.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Inconsistencies Between Proposal Paragraph (a) and RR Time Limits 
Section

    One commenter states there are inconsistencies between the proposed 
changes to the Time Limits Section (TLS) and the Engine Manual (EM) for 
RR Tay model 650-15 and 651-54 series turbofan engines, as follows:
    The GROUP A PARTS MANDATORY INSPECTION TASK number is called out as 
05-20-01-800-001, and in the RR EM the same task number is called out 
as 05-20-01-200-001. Also, in paragraph (2), the reference to ``time 
limits manual T-211(524)-7RR (reference engine manual M-211(524) 7RR)'' 
should read ``time limits manual T-TAY-3RR and T-TAY-5RR (reference 
engine manual E-TAY-3RR and E-TAY-5RR).''
    The FAA agrees that these inconsistencies need to be corrected and 
has made these corrections to the final rule.

Inconsistencies Between Proposal Group A Parts Table and RR TLS

    One commenter states there are inconsistencies between the proposal 
Group A Parts Table and the tabulated components of the RR TLS. One 
inconsistency is that the H.P. Compressor Stage 10 to 11 Rotor Disc 
Spacer nomenclature is not specifically referenced in the Table of the 
proposal, however, its task number appears to have been combined in the 
Table with the H.P. Compressor Stages 8, 9, 10, and 11 Rotor Discs. 
Another inconsistency is that the reference to H.P. Compressor Stage 11 
to 12 Rotor Disc Spacer appears to have been omitted from the proposal 
Table. Also, another inconsistency is that for the H.P. Turbine Stage 2 
Rotor Disc, the overhaul manual task number in the proposal reads ``72-
41-33-200-001'' and in the RR TLS the task number reads ``72-41-33-200-
000.''
    The FAA agrees that these inconsistencies need to be corrected and 
has made these corrections to the final rule.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 700 engines of the affected design in the 
worldwide fleet. The FAA estimates that 448 engines installed on 
aircraft of U.S. registry would be affected by this AD. The FAA also 
estimates that it would take approximately twenty work hours per engine 
to accomplish the inspections, and that the average labor rate is $60 
per work hour. Since this is an added inspection requirement, included 
as part of the normal maintenance cycle, no additional part costs are 
involved. Based on these figures, the total cost of the proposed AD on 
U.S. operators is estimated to be $537,600.

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) 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 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

    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:

[[Page 21980]]

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 adding a new airworthiness directive to 
read as follows:

2002-09-02 Rolls-Royce, plc.: Amendment 39-12735. Docket No. 2001-
NE-36-AD.

Applicability

    This airworthiness directive (AD) is applicable to Rolls-Royce 
plc. Tay Model 650-15 and 651-54 turbofan engines. These engines are 
installed on, but not limited to Boeing 727 and Fokker 100 
airplanes.

    Note 1: This airworthiness directive (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 critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, accomplish the following:
    (a) Within the next 30 days after the effective date of this AD, 
revise the Airworthiness Limitations Section (ALS) and Maintenance 
Scheduling Section (MSS) of the Instructions for Continued 
Airworthiness (ICA) in the Time Limits Manuals publication number 
(P/N) T-TAY-3RR, and T-TAY-5RR of the Engine Manuals, P/N E-TAY-3RR, 
and E-TAY-5RR as applicable, and for air carrier operations revise 
the approved continuous airworthiness maintenance program, by adding 
the following: ``GROUP A PARTS MANDATORY INSPECTION TASK 05-20-01-
200-001
    (1) General: A full inspection of Group A Parts must be effected 
whenever the following conditions are satisfied.
    (i) When the component has been completely disassembled to 
piece-part level in accordance with the appropriate disassembly 
procedures contained in the Engine Manual. and
    (ii) The part has accumulated in excess of 100 flight cycles in 
service or since the last piece-part inspection. or
    (iii) The component removal was for damage or a cause directly 
related to its removal.
    (2) Mandatory inspections for individual Group A Parts are 
specified below: For time limits manual T-TAY-3RR and T-TAY-5RR 
(reference engine manual E-TAY-3RR and E-TAY-5RR) only, insert the 
following Table:

------------------------------------------------------------------------
                                                Inspected per  overhaul
      Part nomenclature           Part No.            manual  task
------------------------------------------------------------------------
Low Pressure Compressor       All............  72-31-11-200-000
 Rotor Disc.
I. P. Compressor Rotor--      All............  72-33-31-200-000
 Stage 1 Disc.
I. P. Compressor Rotor--      All............  72-33-32-200-000
 Stage 2 Disc.
I. P. Compressor Rotor--      All............  72-33-33-200-000
 Stage 3 Disk.
L. P. and I. P. Compressor    All............  72-33-40-200-000
 Drive Shaft.
H. P. Compressor Rear Drive   All............  72-37-31-200-000
 Shaft.
L. P. Compressor Rotor Drive  All............  72-37-32-200-002
 Shaft.
H. P. Compressor Stage 1      All............  72-37-33-200-001
 Rotor Disc.
H. P. Compressor Stages 2     All............  72-37-33-200-002
 and 3 Rotor Discs.
H. P. Compressor Stages 4,    All............  72-37-34-200-000
 5, 6, and 7 Rotor Discs.
H. P. Compressor Stages 8,    All............  72-37-35-200-000
 9, 10, and 11 Rotor Discs.
H.P. Compressor Stage 10 to   All............  72-37-35-200-001
 11 Rotor Disc Spacer.
H. P. Compressor Stage 12     All............  72-37-36-200-001
 Rotor Disc.
H.P. Compressor Stage 11 to   All............  72-37-36-200-003
 12 Rotor Disc Spacer.
H. P. Turbine Shaft.........  All............  72-41-31-200-000
H. P. Stage 1 Rotor Disc....  All............  72-41-32-200-000
H. P. Turbine Stage 2 Rotor   All............  72-41-33-200-000
 Disc.
L. P. Turbine Shaft.........  All............  72-52-21-200-003
L. P. Turbine Stage 1 Rotor   All............  72-52-22-200-000
 Disc.
L. P. Turbine Stage 2 Rotor   All............  72-52-23-200-000
 Disc.
L. P. Turbine Stage 3 Rotor   All............  72-52-24-200-000
 Disc.
------------------------------------------------------------------------

    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
must be performed only in accordance with the TLM and applicable 
Engine Manual.

Alternative Method 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 Engine Certification Office. Operators must 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector (PMI), who may add comments and then send it 
to the Engine Certification Office.

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

    (d) Special flight permits may be issued in accordance with 
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.
    (e) The records of the mandatory inspections required as a 
result of revising the TLM and the applicable Engine Manual and the 
air carrier's continuous airworthiness maintenance program as 
provided by paragraph (a) of this AD must be maintained by FAA-
certificated air carriers which have an approved continuous 
airworthiness maintenance program in accordance with the record 
keeping system currently specified in their manual required by 
sections 121.369 of the Federal Aviation Regulations (14 CFR 
121.369); or, in lieu of the record showing the current status of 
each mandatory inspection required by sections 121.380(a)(2)(vi) of 
the Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)), 
certificated air carriers may establish an approved alternate system 
of record retention that provides a method for preservation and 
retrieval of the maintenance records that include the inspections 
resulting from this AD, and include the policy and procedures for 
implementing this alternate method in the air carrier's maintenance 
manual required by sections 121.369 (c) of the Federal Aviation 
Regulations (14 CFR 121.369 (c)); however, the alternate system must 
be accepted by the appropriate PMI and require the maintenance 
records be maintained either indefinitely or until the work is 
repeated.


[[Page 21981]]


    Note 3: These record keeping requirements apply only to the 
records used to document the mandatory inspections required as a 
result of revising the ALS and the MSS of the Instructions for 
Continued Airworthiness in the Time Limits Manual (Chapter 05-10-00) 
of the Engine Manuals as provided in paragraph (a) of this AD, and 
do not alter or amend the record keeping requirements for any other 
AD or regulatory requirement.

Effective Date

    (f) This amendment becomes effective on June 6, 2002.

    Issued in Burlington, Massachusetts, on April 23, 2002.
Marc J. Bouthillier,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-10549 Filed 5-1-02; 8:45 am]
BILLING CODE 4910-13-P