[Federal Register Volume 64, Number 27 (Wednesday, February 10, 1999)]
[Rules and Regulations]
[Pages 6514-6516]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-3040]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-46-AD; Amendment 39-11033; AD 99-04-09]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Limited Dart Series 
Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Rolls-Royce Limited (R-R) Dart series turboprop 
engines. This action requires initial and repetitive fuel burner fuel 
flow calibration checks, and overhaul or replacement of fuel burners. 
This amendment is prompted by reports of an uncontained engine failure 
and fire due to HPT disk rupture caused by fuel burner failure. The 
actions specified in this AD are intended to prevent HPT disk rupture, 
which can result in an uncontained engine failure, engine fire, and 
damage to the aircraft.

DATES: Effective February 25, 1999.

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 25, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before April 12, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 98-ANE-46-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``9-ad-
[email protected]''. Comments sent via the Internet must contain the 
docket number in the subject line.
    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. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the Federal Aviation Administration (FAA) that an unsafe 
condition may exist on Rolls-Royce Limited (R-R) Dart 525 series, 526, 
527, 528 series, 529 series, 530, 531, 532 series, 535 series, 542 
series, and 552 series turboprop engines. The CAA advises that they 
have received a report of an uncontained engine failure and subsequent 
fire shortly after takeoff. The investigation revealed that the high 
pressure turbine (HPT) disk had failed resulting in the release of a 
section of rim and diaphragm from the disk. The cause of the HPT disk 
failure was attributed to high cycle fatigue (HCF) induced by a once-
per-revolution resonance force resulting from fuel burner malfunction. 
This condition, if not corrected, could result in HPT disk rupture, 
which can result in an uncontained engine failure, engine fire, and 
damage to the aircraft.
    R-R has issued Alert Service Bulletin (ASB) No. Da73-A87, dated May 
1998, that specifies procedures for fuel burner fuel flow calibration 
checks and overhaul of fuel burners. The CAA classified the ASB as 
mandatory and issued CAA AD 002-05-98 in order to assure the 
airworthiness of these engines in the UK.

[[Page 6515]]

    This engine model is manufactured in the UK and is type 
certificated for operation in the United States under the provisions of 
section 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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design installed on 
aircraft registered in the United States, this AD requires initial and 
repetitive fuel burner fuel flow calibration checks, and overhaul or 
replacement of fuel burners. The fuel burner fuel flow calibration 
checks, and overhaul or replacement of fuel burners must be performed 
in accordance with the schedule specified in the compliance section. 
The schedule was determined based upon R-R risk analysis, and parts and 
overhaul facility availability.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-ANE-46-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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 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:

    99-04-09  Rolls-Royce Limited: Amendment 39-11033. Docket 98-
ANE-46-AD.

    Applicability: Rolls-Royce Limited (R-R) Dart 525 series, 526, 
527, 528 series, 529 series, 530, 531, 532 series, 535 series, 542 
series, and 552 series turboprop engines, installed on but not 
limited to Gulfstream Aerospace Corp. G-159, British Aerospace HS 
748, Fokker Aircraft F27, Fairchild Hiller FH227, Mitsubishi Heavy 
Industries YS-11, General Dynamics (Convair) 640 and 600 series, and 
Vickers Armstrong (Aircraft Limited) Viscount aircraft.

    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 (e) 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 high pressure turbine (HPT) disk rupture, which can 
result in an uncontained engine failure, engine fire, and damage to 
the aircraft, accomplish the following:
    (a) For engines with a complete set of HPT blades that were 
either inspected and reworked to D.R.S. 611 standard or were 
installed new at last HPT rework or engine overhaul, perform fuel 
burner fuel flow calibration checks and overhaul or replacement of 
fuel burners in accordance with R-R Alert Service Bulletin (ASB) No. 
Da73-A87, dated May 1998, at each engine overhaul, or prior to 
exceeding 3,000 hours time in service (TIS) since last fuel burner 
calibration, whichever occurs first.
    (b) Inspection to the D.R.S. 611 standard requires the HPT 
blades to have both the inner platform and shroud inspected to this 
standard. This inspection requirement was added to the Engine 
Overhaul Manual in 1992. Inspection to the D.R.S. 611 standard prior 
to this date must be considered to be pre-D.R.S. 611 standard.
    (c) For engines with HPT blades that have not been inspected and 
modified during the last engine or HPT overhaul using the D.R.S. 611 
build standard, perform initial and repetitive fuel burner fuel flow 
calibration checks and overhaul or replacement of fuel burners in 
accordance with R-R ASB No. Da73-A87, dated May 1998, as follows:
    (1) For engines with 6,000 or more hours time in service (TIS) 
since last HPT overhaul and rework, perform the initial check and 
overhaul as follows:

[[Page 6516]]

    (i) For fuel burners with more than 850 hours TIS since last 
fuel burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding an additional 150 hours TIS after the 
effective date of this AD, but not to exceed 1,000 hours TIS since 
last fuel burner calibration after June 30, 1999.
    (ii) For fuel burners with 850 or less hours TIS since last fuel 
burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding 1,000 hours TIS since last fuel burner 
calibration.
    (2) For engines with 5,000 or more hours but less than 6,000 
hours TIS since last HPT overhaul and rework, perform the initial 
check and overhaul as follows:
    (i) For fuel burners with more than 700 hours TIS since last 
fuel burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding an additional 300 hours TIS after the 
effective date of this AD, but not to exceed 1,000 hours TIS since 
last fuel burner calibration after June 30, 1999.
    (ii) For fuel burners with 700 or less hours TIS since last fuel 
burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding 1,000 hours TIS since last fuel burner 
calibration.
    (3) For engines with 4,000 or more hours but less than 5,000 
hours TIS since last HPT overhaul and rework, perform the initial 
check and overhaul as follows:
    (i) For fuel burners with more than 550 hours TIS since last 
fuel burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding an additional 450 hours TIS after the 
effective date of this AD, but not to exceed 1,000 hours TIS since 
last fuel burner calibration after June 30, 1999.
    (ii) For fuel burners with 550 or less hours TIS since last fuel 
burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding 1,000 hours TIS since last fuel burner 
calibration.
    (4) For engines with less than 4,000 hours TIS since last HPT 
overhaul and rework, perform the initial check and overhaul as 
follows:
    (i) For fuel burners with more than 100 hours TIS since last 
fuel burner calibration, perform the fuel flow check and calibration 
prior to exceeding an additional 900 hours TIS after the effective 
date of this AD, but not to exceed 1,000 hours TIS since last fuel 
burner calibration after June 30, 1999.
    (ii) For fuel burners with 100 or less hours TIS since last fuel 
burner calibration, perform the fuel flow calibration check and 
overhaul prior to exceeding 1,000 hours TIS since last fuel burner 
calibration.
    (5) Thereafter, perform repetitive fuel burner fuel flow 
calibration checks and overhauls at intervals not to exceed 1,000 
hours TIS since last fuel burner fuel flow calibration check.
    (d) After the effective date of this AD, no new fuel burner may 
be installed unless it has been subject to a satisfactory fuel flow 
calibration check within 3 years prior to installation, and no fuel 
burner run since last overhaul, including those fitted to a 
combustion chamber, may be installed unless it has been subject to a 
satisfactory fuel flow calibration check in accordance to R-R ASB Da 
73-A87, dated May 1998, prior to installation.
    (e) 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. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, 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.

    (f) Special flight permits may be issued in accordance with 
sections 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.
    (g) The actions required by this AD shall be performed in 
accordance with the following R-R ASB:

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             Document No.                Pages             Date
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Da73-A87..............................      1-8  May 1998.
    Total pages: 8.
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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. 
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.
    (h) This amendment becomes effective on February 25, 1999.

    Issued in Burlington, Massachusetts, on February 2, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-3040 Filed 2-9-99; 8:45 am]
BILLING CODE 4910-13-U