[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:

----------------------------------------------------------------------------------------------------------------
                       Document No.                            Pages         Revision               Date        
----------------------------------------------------------------------------------------------------------------
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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