Airworthiness Directives; Rolls-Royce Spey 555-15, -15H, -15N, and -15P Turbofan Engines

[Federal Register Volume 65, Number 221 (Wednesday, November 15, 2000)]
[Rules and Regulations]
[Pages 68875-68876]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-28960]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-03-AD; Amendment 39-11981; AD 2000-23-11]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Spey 555-15, -15H, -15N, 
and -15P Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Rolls-Royce (RR) plc. Spey 555-15, -15H, -15N, and -15P 
turbofan engines, that requires modification of the low pressure (LP) 
turbine stage 2 nozzle guide vane (NGV) support ring seal assembly. 
This amendment is prompted by two instances of disk drive arm damage. 
In both cases, heavy damage to the stage 1 LP turbine-to-stage 2 LP 
turbine disk drive arm occurred as a result of an out-of-balance 
condition following the failure of a stage 2 LP turbine blade. The 
actions specified by this AD are intended to prevent damage to the disk 
drive arm which could result in loss of stage 1 LP turbine-to-stage 2 
LP turbine disk drive, a turbine overspeed condition, and possible 
uncontained disk failure and damage to the airplane.

DATES: Effective date December 20, 2000. The incorporation by reference 
of certain publications listed in the rule is approved by the Director 
of the Federal Register as of December 20, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone No. 011-44-1332-242-424; FAX No. 011-44-1332-245-418. This 
information may be examined 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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone No. 
781-238-7176; fax No. 781-238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Rolls-Royce (RR) plc. Spey 555-15, 
-15H, -15N, and -15P turbofan engines was published in the Federal 
Register on July 7, 2000 (65 FR 41884). That action proposed to require 
modification of the low pressure (LP) turbine stage 2 nozzle guide vane 
(NGV) support ring seal assembly in accordance with Service Bulletin 
(SB) No. Sp 72-1063, dated May 1999.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Economic Impact

    There are approximately 310 engines of the affected design in the 
worldwide fleet. The FAA estimates that 60 engines installed on 
aircraft of U.S. registry would be affected by this AD. It will take 
approximately 2.0 work hours per engine to accomplish the proposed 
actions. The average labor rate is $60 per work hour. Since this action 
is a rework of existing parts, there is no required parts cost. Based 
on these figures, the FAA estimates the total cost impact of the 
proposed AD on U.S. operators to be $7,200.

Regulatory Impact

    This proposed rule does not have federalism implications, as 
defined in Executive Order No. 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 action (1) Is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air Transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 Code of Federal 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:

2000-23-11  Rolls-Royce: Amendment 39-11981. Docket 2000-NE-03-AD.

    Applicability: Rolls-Royce (RR) plc. Spey 555-15, -15H, -15N, 
and -15P turbofan engines. These engines are installed on but not 
limited to Fokker F.28 Mark series 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 (b) 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: Required as indicated, unless accomplished 
previously.
    To prevent damage to the disk drive arm which could result in 
loss of stage 1 LP turbine-to-stage 2 LP turbine disk drive, a 
turbine overspeed condition and possible uncontained disk failure, 
and damage to the airplane, do the following:

Rework Instructions

    (a) Within three years after the effective date of this AD, 
rework the low pressure (LP) turbine stage 2 nozzle guide vane (NGV) 
support ring seal assembly in accordance with paragraphs 2.A. 
through 2.C. of the Accomplishment Instructions of RR service

[[Page 68876]]

bulletin (SB) No. Sp 72-1063, dated May 1999.

Alternative Methods of Compliance

    (b) 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 shall 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

    (c) 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 aircraft to a location where the 
requirements of this AD can be accomplished.
    (d) The rework shall be done in accordance with the following 
Rolls-Royce service bulletin: (SB) No. Sp 72-1063, dated May 1999. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Rolls-Royce plc, PO Box 31, Derby, 
England, DE248BJ; telephone No. 011-44-1332-242-424; fax No. 011-44-
1332-245-418. Copies may be inspected 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.

Effective Date of This AD

    (e) This amendment becomes effective on December 20, 2000.

    Issued in Burlington, Massachusetts, on November 6, 2000.
Donald Plouffe,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-28960 Filed 11-14-00; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:35:00.773042+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

d9d6884e4a392e0e260e5c9c3eaf0d0f4f854276406a7753177428523cb09d38

Text SHA-256

07adf9aac07901824cf1c37accebd69bf931284c880ada93bca2c8482a15d13d