[Federal Register Volume 60, Number 115 (Thursday, June 15, 1995)]
[Rules and Regulations]
[Pages 31388-31389]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14638]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-ANE-20; Amendment 39-9270; AD 95-12-19]
Airworthiness Directives; Pratt & Whitney JT8D-200 Series
Turbofan 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 Pratt & Whitney (PW) JT8D-200 series turbofan engines.
This action requires periodic inspection of fan blades for locked fan
blade shrouds and foreign object damage (FOD); unlocking of fan blade
shrouds, if necessary; and lubrication of fan blade shrouds. This
amendment is prompted by reports of six recent fan blade failures, two
of which resulted in the separation of the engine nose cowl from the
aircraft. The actions specified in this AD are intended to prevent fan
blade failure, which can result in damage to the aircraft.
DATES: Effective June 30, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 30, 1995.
Comments for inclusion in the Rules Docket must be received on or
before August 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-ANE-20, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
Pratt & Whitney, 400 Main St., East Hartford, CT 06108. This
information may be examined at the FAA, New England Region, Office of
the Assistant Chief 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: Mark A. Rumizen, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7137, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received six recent reports of engine failures due to fan blade
failures on Pratt & Whitney (PW) JT8D-200 series turbofan engines. Fan
blade failures can have serious secondary effects such as inlet cowl
penetration or liberation, engine flange separation, fuel leaks, or
impact damage to the aircraft. Most of these failures result from
fractures that originate in the leading edge of the blade just above
the platform. The FAA has determined that the primary cause of the
failures is high cycle fatigue (HCF) cracking that is initiated by
foreign object damage (FOD) to this area of the blade. Other factors
have been found to increase the blade stresses such that the blade is
more susceptible to FOD induced HCF cracking. These factors include
locked fan blade shrouds, which increase blade stresses, and leading
edge erosion, which can produce blade flutter. This condition, if not
corrected, could result in fan blade failure, which can result in
damage to the aircraft.
The FAA has reviewed and approved the technical contents of PW All
Operators Wire (AOW) No. JT8D/72-33/CTS: CRC-5-4-5-1, dated April 5,
1995, that describes procedures for periodic inspection of fan blades
for locked rotors and FOD; unlocking of fan blade shrouds, if
necessary; and lubrication of fan blade shrouds.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design, this
airworthiness directive (AD) is being issued to prevent fan blade
failure, which can result in damage to the aircraft. This AD requires
periodic inspection of fan blades for locked rotors and FOD; unlocking
of fan blade shrouds, if necessary; and lubrication of fan blade
shrouds. The actions are required to be accomplished in accordance with
the AOW described previously.
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
[[Page 31389]] 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 95-ANE-20.'' 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-12-19 Pratt & Whitney: Amendment 39-9270. Docket 95-ANE-20.
Applicability: Pratt & Whitney (PW) Models JT8D-209, -217, -
217A, -217C, and -219 turbofan engines that have installed fan
blades, Part Numbers 798821, 798821-001, 808121, 808121-001, 809221,
811821, 851121, 851121-001, 5000021-02, 5000021-022, and 5000021-
032. These engines are installed on but not limited to McDonnell
Douglas MD-80 series aircraft.
Note: 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 use the
authority provided in paragraph (b) to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any engine from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fan blade failure, which can result in damage to the
aircraft, accomplish the following:
(a) Inspect fan blades and shrouds, unlock fan blade shrouds,
and lubricate fan blade shrouds, in accordance with the intervals
and procedures described in Parts 1 and 2 of PW All Operators Wire
(AOW) No. JT8D/72-33/CTS: CRC-5-4-5-1, dated April 5, 1995.
(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. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(c) 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.
(d) The requirements of this AD shall be done in accordance with
the following service document:
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Document no. Pages Date
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PW AOW No. JT8D/72-33/CTS: CRC-5-4-5-1...... 1-5 April 5, 1995.
Total pages: 5.
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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 Pratt & Whitney, 400 Main St., East
Hartford, CT 06108. Copies may be inspected at the FAA, New England
Region, Office of the Assistant Chief 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.
(e) This amendment becomes effective on June 30, 1995.
Issued in Burlington, Massachusetts, on June 5, 1995.
Ronald L. Vavruska,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 95-14638 Filed 6-13-95; 9:16 am]
BILLING CODE 4910-13-U
