[Federal Register Volume 60, Number 23 (Friday, February 3, 1995)]
[Rules and Regulations]
[Pages 6654-6657]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-2405]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-ANE-40; Amendment 39-9135; AD 95-02-16]
Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Pratt & Whitney (PW) JT8D series turbofan
engines, that currently requires initial and repetitive inspections of
the Number 7 fuel nozzle and support assembly, replacement of the
Number 7 fuel nozzle and support assembly with a more leak-resistant
configuration, and replacement of aluminum oil pressure and scavenge
tube fittings with steel fittings. This amendment adds a requirement
incorporated in a new revision of a PW Alert Service Bulletin (ASB)
that was omitted from the existing AD to replace an additional aluminum
oil scavenge line bolt with a steel bolt. This amendment also makes a
correction to a note in the compliance section to apply only to PW
JT8D-200 series engines. This amendment is prompted by the need to make
these corrections. The actions specified by this AD are intended to
prevent fuel leakage from the Number 7 fuel nozzle and support
assembly, ignition of that leaking fuel, and liberation of oil from
melted oil line fittings, which can result in an uncontained engine
fire and damage to the aircraft.
DATES: Effective February 21, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 21, 1995.
Comments for inclusion in the Rules Docket must be received on or
before April 4, 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. 94-ANE-40, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
Pratt & Whitney, Technical Publications Department, M/S 132-30, 400
Main Street, East Hartford, CT 06108. This information may be examined
at the FAA, New England Region, Office of the Assistant Chief Counsel,
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: On June 29, 1994, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 94-14-16,
Amendment 39-8964 (59 FR 35238, July 11, 1994), applicable to Pratt &
Whitney (PW) JT8D series turbofan engines, to require inspection of the
Number 7 fuel nozzle and support assembly for evidence of fuel leakage
and burning until replacement of the Number 7 fuel nozzle and support
assembly with an improved sealing configuration. That AD also requires
replacement of the aluminum oil tube fittings with steel fittings. That
action was prompted by two reports of uncontained engine fires on Pratt
& Whitney (PW) JT8D series engines due to fuel leakage from the Number
7 fuel nozzle and support assembly, ignition of that fuel, melting of
aluminum oil pressure and scavenge tube fittings that are in the
proximity of the Number 7 nozzle, and augmentation of that fire with
the liberated oil. The resulting fire burned through the engine
diffuser case and fan ducts, causing an aircraft engine cowl fire. That
condition, if not corrected, could result in fuel leakage from the
Number 7 fuel nozzle and support assembly, ignition of that leaking
fuel, and liberation of oil from melted oil line fittings, which can
result in an uncontained engine fire and damage to the aircraft.
Since the issuance of that AD, the FAA noted the omission of the
requirement to replace an additional aluminum oil scavenge line bolt
with a steel bolt. This additional requirement is incorporated in
Revision 2 to PW Alert Service Bulletin (ASB) No. A6170, dated October
20, 1994. Also, the FAA was alerted of an error in the compliance
section where the incorrect engine series was specified. In paragraph
(b)(2)(iv), the reference to ``all other JT8D engines'' should read
``JT8D-200 series engines.'' In addition, PW has issued Revision 2 to
ASB No. A6169, dated October 26, 1994, which differs from Revision 1,
cited in the current AD, only by minor, non-substantive changes.
The FAA has reviewed and approved the technical contents of PW ASB
No. A6153, Revision 1, dated June 8, 1994, that describes procedures
for initial and repetitive borescope inspections of the Number 7 fuel
nozzle and support assembly; and PW ASB A6170, Revision 2, dated
October 20, 1994, and ASB No. A6169, Revision 2, dated October 26,
1994, that describe procedures for replacement of the Number 7 fuel
nozzle and support assembly with a more leak-resistant configuration
and replacement of the aluminum oil tube fittings with steel fittings,
respectively.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
supersedes AD 94-14-16 to continue to require inspection
[[Page 6655]] of the Number 7 fuel nozzle and support assembly for
evidence of fuel leakage and burning until replacement of the Number 7
fuel nozzle and support assembly with an improved sealing
configuration. This AD also requires replacement of the aluminum oil
tube fittings with steel fittings. In addition, this AD adds a
requirement incorporated in PW ASB No. 6170, Revision 2, dated October
20, 1994, that was omitted from AD 94-14-16 to replace an additional
aluminum oil scavenge line bolt with a steel bolt, and makes a
correction to paragraph (b)(2)(iv). The actions are required to be
accomplished in accordance with the alert service bulletins 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 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 94-ANE-40.'' 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 removing Amendment 39-8964, (59 FR
35238, July 11, 1994), and by adding a new airworthiness directive,
Amendment 39-9135, to read as follows:
95-02-16 Pratt & Whitney: Amendment 39-9135. Docket 94-ANE-40.
Supersedes AD 94-14-16, Amendment 39-8964.
Applicability: Pratt & Whitney (PW) Model JT8D-209, -217, -217A,
-217C, -219 turbofan engines; and JT8D-1, -1A, -1B, -7, -7A, -7B, -
9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines
incorporating the original issue or any revision of Pratt & Whitney
Service Bulletin No. 5650; and any PW Model JT8D engine with low
emissions fuel nozzles, Part Numbers 775485, 809137-01, 802965, and
5004308-02 installed. These engines are installed on but not limited
to Boeing 727 and 737 series, and McDonnell Douglas DC-9 and MD-80
series aircraft.
Compliance: Required as indicated, unless accomplished previously.
To prevent fuel leakage from the Number 7 fuel nozzle and support
assembly and melting of the oil pressure and scavenge tube fittings,
which can result in an uncontained engine fire and damage to the
aircraft, accomplish the following:
(a) Inspect Number 7 fuel nozzle and support assemblies in
accordance with PW Alert Service Bulletin (ASB) No. A6153, Revision
1, dated June 8, 1994, as follows:
(1) For Number 7 fuel nozzle and support assemblies that have
accumulated more than 2,500 hours time in service (TIS) since last
fuel nozzle and support assembly overhaul on the effective date of
this airworthiness directive (AD), initially inspect for fuel
leakage within 700 hours TIS after the effective date of this AD.
(2) For engines with Number 7 fuel nozzle and support assemblies
with 2,500 or less hours TIS since fuel nozzle and support assembly
overhaul on the effective date of this AD, initially inspect prior
to accumulating 3,200 hours TIS since overhaul.
(3) Thereafter, inspect for fuel leakage in accordance with PW
ASB A6153, Revision 1, dated June 8, 1994, at intervals not to
exceed 700 hours TIS since last inspection.
(4) Remove from service Number 7 fuel nozzle and support
assemblies that exhibit evidence of fuel leakage as described in PW
ASB No. A6153, Revision 1, dated June 8, 1994, and replace with the
improved sealing configuration nozzle in accordance with paragraph
(b) of this AD, as follows:
(i) Within 25 hours TIS, or 25 cycles in service (CIS),
whichever occurs first, after the inspection performed in paragraph
(a)(1), (a)(2), or (a)(3) for aircraft with only one engine
exhibiting Number 7 fuel nozzle and support assembly leakage.
(ii) Prior to further flight, on aircraft with two engines
exhibiting Number 7 fuel nozzle and support assembly leakage, remove
and replace at least one of the leaking Number 7 fuel nozzle and
support assemblies. The remaining Number 7 fuel nozzle and support
assembly that exhibits leakage shall be removed and replaced in
accordance with paragraph (a)(4)(i) of this AD.
(iii) Prior to further flight, on Boeing 727 aircraft, with
three engines exhibiting Number 7 fuel nozzle and support assembly
leakage, remove and replace at least two of the leaking Number 7
fuel nozzle and support assemblies. The remaining Number 7 fuel
nozzle and support assembly that [[Page 6656]] exhibits leakage
shall be removed and replaced in accordance with paragraph (a)(4)(i)
of this AD.
Note: Fuel nozzles and support assemblies that have not
undergone overhaul do not require inspection in accordance with
paragraph (a) of this AD.
(b) At the next accessibility of the diffuser build group after
the effective date of this AD, but no later than July 31, 1999,
accomplish the following:
(1) Replace the Number 7 fuel nozzle and support assembly with
the improved sealing configuration in accordance with Part 1 of PW
ASB No. A6169, Revision 2, dated October 26, 1994.
(2) Replace the aluminum pressure and scavenge oil tube fittings
with steel fittings in accordance with PW ASB No. A6170, Revision 2,
dated October 20, 1994.
Note: Replacement of the following oil tubes with corresponding
oil tubes that incorporate steel fittings constitutes compliance
with paragraph (b)(2) of this AD:
(i) Outer internal Number 4 and 5 bearing pressure tube assembly
for PW JT8D-200 series engines.
(ii) Outer internal main bearing pressure tube assembly for PW
JT8D-200 series engines.
(iii) Main bearing pressure manifold assembly for PW JT8D-200
series engines.
(iv) Front Number 4\1/2\ and 6 bearing pressure tube assembly
for JT8D-200 series engines.
(v) Number 4 bearing oil scavenge tube assembly for all other
JT8D engines.
(vi) Number 4 bearing oil pressure tube assembly for all other
JT8D engines.
(vii) Main bearing pressure manifold assembly for all other JT8D
engines.
(c) Incorporation of the hardware required by paragraph (b)(1)
of this AD, constitutes terminating action for the inspections
required by paragraph (a) of this AD.
(d) For the purpose of this AD, accessibility of the diffuser
build group is defined as engine maintenance that entails flange
separation of the diffuser case from the combustion chamber outer
case.
(e) For the purpose of this AD, fuel nozzle and support assembly
overhaul is defined as disassembly of the fuel nozzle from the
support assembly that entails removal of the fuel nozzle nut.
(f) For any Number 7 fuel nozzle and support assembly that is
removed for evidence of leakage in accordance with paragraph (a) of
this AD, submit the following information within 60 days after the
removal, to the Manager, Engine Certification Office, Engine and
Propeller Directorate, Aircraft Certification Service, FAA, 12 New
England Executive Park, Burlington, Massachusetts, 01803-5299; fax
(617) 238-7199:
(1) Fuel nozzle and support assembly part number and serial
number.
(2) Fuel nozzle and support assembly time and cycles since
overhaul.
(3) Description of fuel nozzle and support assembly distress.
(4) Position of distressed fuel nozzle and support assembly.
(5) Description of any other resultant engine damage.
(6) Engine serial number.
(7) Engine time and cycles since overhaul.
The reporting requirements of this AD terminate after compliance
with paragraph (b)(1) of this AD. Information collection
requirements contained in this regulation have been approved by the
Office of Management and Budget (OMB) under the provision of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501-3520) and have been
assigned OMB Control Number 2120-0056.
(g) 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.
(h) 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.
(i) The inspections and modifications shall be done in
accordance with the following service documents:
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Document No. Pages Revision Date
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PW ASB No. A6153.......................................... 1-4 1................. June 8, 1994.
5 Original.......... Feb. 4, 1994.
6-8 1................. June 8, 1994.
9-12 Original.......... Feb. 4, 1994.
Total pages: 12.
PW ASB No. A6169.......................................... 1 2................. Oct. 26, 1994.
2-6 1................. June 15, 1993.
7 Original.......... Apr. 29, 1993.
8 2................. Oct. 26, 1994.
9-16 Original.......... Apr. 29, 1993.
17 1................. June 15, 1994.
18-29 Original.......... Apr. 29, 1993.
30-31 2................. Oct. 26, 1994.
Total pages: 31.
PW ASB No. A6170.......................................... 1 2................. Oct. 20, 1994.
2-3 1................. Sept. 9, 1994.
4-5 2................. Oct. 20, 1994.
6-7 1................. Sept. 9, 1994.
8 2................. Oct. 20, 1994.
9 Original.......... May 13, 1994.
10 2................. Oct. 20, 1994.
11-13 Original.......... May 13, 1994.
14 2................. Oct. 20, 1994.
15-18 1................. Sept. 9, 1994.
19-21 2................. Oct. 20, 1994.
22 1................. Sept. 9, 1994.
Total pages: 22.
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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, Technical
Publications Department, M/S 132-30, 400 Main Street, 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.
(j) This amendment becomes effective on February 21, 1995.
[[Page 6657]] Issued in Burlington, Massachusetts, on January
24, 1995.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 95-2405 Filed 2-2-95; 8:45 am]
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