AD 2000-12-18

[Federal Register Volume 65, Number 123 (Monday, June 26, 2000)]
[Rules and Regulations]
[Pages 39286-39288]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-15424]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-50-AD; Amendment 39-11796; AD 2000-12-18]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Ltd. Dart 511, 511-7E, 514-
7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-7R, 
551-7R, and 552-7R Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Rolls-Royce Ltd. Dart 511, 511-7E, 514-7, 528, 528-7E, 
529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-7R, 551-7R, and 552-
7R turboprop engines. This AD requires the installation of a feathering 
probe and a steel retaining ring in the reduction gear housing (RGH) 
and replacement of a transfer bobbin installed in the torquemeter. This 
amendment is prompted by two reports of the failure of a propeller to 
feather following the failure of the RGH annulus gear, which resulted 
in the propeller overspeeding and the release of a propeller blade, 
causing damage to the airplane. The actions specified by this AD are 
intended to prevent a propeller from overspeeding and the release of a 
propeller blade after a failure of the RGH annulus gear, which could 
result in damage to an adjacent engine or to the airplane.

DATES: Effective date July 31, 2000. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of July 31, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce Limited, Attn: Dart Engine Service Manager, 
East Kilbride, Glasgow G74 4PY, Scotland; telephone: 011-44-1355-220-
200, fax: 011-44-1141-778-432. 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: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone 781-238-
7747, fax 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) applicable to Rolls-Royce Ltd. (R-R) Dart 511, 511-7E, 
514-7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-
7R, 551-7R, and 552-7R turboprop engines was published in the Federal 
Register on January 12, 2000 (65 FR 1840). That action proposed to 
require:
    <bullet> Installation of a feathering probe.
    <bullet> Installation of a steel retaining ring in the reduction 
gear housing.
    <bullet> Replacement of a torquemeter oil pressure transfer bobbin.

The actions will be required to be accomplished at the next shop visit 
after the effective date of the AD, or by December 31, 2000, whichever 
occurs first, in accordance with R-R service bulletin (SB) Da72-348, 
Revision 13, dated April 1999.

Conclusion

    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 economic analysis. The FAA has determined that 
air safety and the public interest require the adoption of the rule as 
proposed.

Economic Impact

    There are approximately 1500 engines of the affected design in the 
worldwide fleet. The FAA estimates that 100 engines installed on 
aircraft of U.S. registry would be affected by this AD, that it would 
take approximately two work hours per engine to accomplish the actions, 
and that the average labor rate is $60 per work hour. Required parts 
would cost approximately $300 per engine. Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$42,000.

Regulatory Impact

    This rule does not have federalism implications, as defined in 
Executive Order 13132, because it will 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 rule.
    For the reasons discussed above, I certify that this regulation (1) 
is not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a

[[Page 39287]]

``significant rule'' under the 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 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, 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 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:

2000-12-18  Rolls Royce Ltd.: Amendment 39-11796, Docket No. 99-NE-
50-AD.
    Applicability: This AD is applicable to Rolls-Royce Ltd. (R-R) 
Dart 511, 511-7E, 514-7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 
532-7P, 532-7R, 535-7R, 551-7R, and 552-7R turboprop engines. These 
engines are installed on but not limited to Fokker Aircraft B.V. F27 
series and Maryland Air Industries (formerly Fairchild) F-27 and FH-
227 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 (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 
below, unless already completed.
    To prevent a propeller from overspeeding, resulting in propeller 
release after a failure of the annulus gear, which could result in 
damage to an adjacent engine or to the airplane, do the following:

Installation of a Sensor Probe and Retaining Ring

    (a) At the next shop visit after the effective date of this AD, 
or by December 31, 2000, whichever occurs first, do all of the 
following:
    (1) Install a feathering probe in the front bearing panel of the 
reduction gearbox in accordance with paragraph 2.A. of service 
bulletin (SB) Da72-348, revision 13, dated April 13, 1999.
    (2) Install a steel retaining ring between the nose casing and 
the front bearing panel in accordance with paragraph 2.C. of SB 
Da72-348, revision 13, dated April 13, 1999.
    (3) Replace the existing transfer bobbin with an aluminum bobbin 
in accordance with paragraph 2.C. of SB Da72-348, revision 13, dated 
April 13, 1999.

Definition of a Shop Visit

    (b) For the purposes of this AD, a shop visit is defined as any 
maintenance action that results in the removal or disassembly of the 
reduction gearbox.

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 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

    (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 aircraft to a location where the 
requirements of this AD can be accomplished.

Documents Incorporated by Reference

    (e) The inspection shall be done in accordance with the 
following Rolls-Royce service bulletin:

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          Document No.                     Pages                   Revision                     Date
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                                (The original service bulletin omitted page 8.)
Da72-348.......................  1-2, 2A/2B..............  13.....................  Apr. 1999.
                                 3.......................  7......................  Aug. 22, 1969.
                                 4-7.....................  Original...............  Dec. 24, 1968.
                                 9.......................  11.....................  July 10, 1970.
                                 9A......................  11.....................  July 10, 1970.
                                 10-12...................  11.....................  July 10, 1970.
                                 12A-12B.................  11.....................  July 10, 1970.
                                 13......................  11.....................  July 10, 1970.
                                 14-16...................  Original...............  Dec. 24, 1968.
                                 17......................  4......................  May 16, 1969.
                                 18-19...................  Original...............  Dec. 24, 1968.
                                 20-20A..................  10.....................  Jan. 23, 1970.
                                 21......................  6......................  July 11, 1969.
                                 22......................  Original...............  Dec. 24, 1968.
                                 23......................  11.....................  July 10, 1970.
                                 24......................  Original...............  Dec. 24, 1968.
                                 25-26...................  13.....................  Apr. 1999.
Supplement.....................  1-2.....................  Original...............  Feb. 7, 1969.
    Total pages: 32
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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 Limited, Attn: Dart 
Engine Service Manager, East Kilbride, Glasgow G74 4PY, Scotland; 
telephone: 011-44-1355-220-200, fax: 011-44-1141-778-432. 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,

[[Page 39288]]

800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date of This AD

    (f) This amendment becomes effective on July 31, 2000.

    Issued in Burlington, Massachusetts, on June 9, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-15424 Filed 6-23-00; 8:45 am]
BILLING CODE 4910-13-U