[Federal Register Volume 59, Number 131 (Monday, July 11, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-16399]
[[Page Unknown]]
[Federal Register: July 11, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-ANE-27; Amendment 39-8964; AD 94-14-16]
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 adopts a new airworthiness directive (AD) that
is applicable to certain Pratt & Whitney (PW) JT8D series engines. This
action 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 is prompted by reports of two engine
fires initiated by 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 actions specified in 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 July 26, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 26, 1994.
Comments for inclusion in the Rules Docket must be received on or
before September 9, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket Number 94-ANE-27, 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,
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 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. The FAA has determined
that the fuel nozzle and support assembly is susceptible to incomplete
or improper refurbishment or repair that could result in fuel leaks
across the fuel nozzle seals, and that the aluminum oil pressure and
scavenge tube fittings have inadequate fire resistance capability.
These oil line fittings are in the path of the fuel leaking and
associated fire from the Number 7 fuel nozzle and support assembly.
Impingement of the fire on these oil fittings causes them to melt, thus
causing the oil contained in the oil tubes to escape and to augment the
fire. Therefore, this amendment will require the 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 a more leak-resistant configuration. It also requires
replacement of the aluminum oil tube fittings with steel fittings. This
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.
The FAA has reviewed and approved the technical contents of PW
Alert Service Bulletin (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 ASB
No. A6169, Revision 1, dated June 15, 1994, and A6170, dated May 13,
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 PW JT8D series engines of the same type
design, this AD is being issued to prevent uncontained engine fire and
damage to the aircraft. This AD requires 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. This AD also requires
replacement of the aluminum oil tube fittings with steel fittings. 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-27.'' 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:
94-14-16 Pratt & Whitney: Amendment 39-8964. Docket 94-ANE-27.
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 exhibits leakage shall be removed
and replaced in accordance with paragraph (a)(4)(i) of this AD.
Note: Fuel nozzles 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 1, dated June 15, 1994.
(2) Replace the aluminum pressure and scavenge oil tube fittings
with steel fittings in accordance with PW ASB No. A6170, dated May
13, 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 all other JT8D 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
Sec. Sec. 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.... February 4, 1994.
6-8 1........... June 8, 1994.
9-12 Original.... February 4, 1994.
Total pages: 12.
PW ASB No. A6169.......... 1-6 1........... June 15, 1994.
7-16 Original.... April 29, 1994.
17 1........... June 15, 1994.
1-30 Original.... April 29, 1994.
Total pages: 30.
PW ASB No. A6170.......... 1-20 Original.... May 13, 1994.
Total pages: 20.
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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 July 26, 1994.
Issued in Burlington, Massachusetts, on June 29, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-16399 Filed 7-8-94; 8:45 am]
BILLING CODE 4910-13-P
