[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: ``engineprop@faa.gov''. 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
