[Federal Register Volume 59, Number 197 (Thursday, October 13, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-24200]


[[Page Unknown]]

[Federal Register: October 13, 1994]


-----------------------------------------------------------------------


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-ANE-83; Amendment 39-9036; AD 94-20-08]

 

Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

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 
installed third and fourth stage low pressure turbine (LPT) blade sets 
for blade shroud crossnotch wear, and removal of blade sets found with 
excessively worn blade shroud crossnotches. This amendment continues to 
require inspections, and removal, if necessary, of blade sets, but also 
requires, as a terminating action to the inspections: installation of 
improved LPT containment hardware, and installation of an improved No. 
6 bearing scavenge pump bracket bushing. This amendment is prompted by 
reports of additional uncontained engine failures since publication of 
the current AD, and the availability of improved LPT containment 
hardware. The actions specified by this AD are intended to prevent 
damage to the aircraft resulting from engine debris following an LPT 
blade or shaft failure.

DATES: Effective on November 14, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 14, 1994.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main Street, East Hartford, CT 
06108. This information may be examined at the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, 12 New England Executive Park, Burlington, MA 01803-5299; 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 May 24, 1993, the Federal Aviation 
Administration (FAA) issued airworthiness directive (AD) 93-06-05, 
Amendment 39-8530 (58 FR 31902, June 1, 1993), applicable to Pratt & 
Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -17, 
and -17R engines, to require initial and repetitive inspections of the 
third and fourth stage low pressure turbine (LPT) blade sets for 
excessively worn blade shroud crossnotches, and the removal of blade 
sets found with excessively worn blade crossnotches. That AD is not 
applicable, however, to PW JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -
11, -15, -17, and -17R engines that contain fan exhaust inner front 
duct segment assemblies that are installed in accordance with PW Alert 
Service Bulletin (ASB) No. 6039, Revision 2, dated May 4, 1992, or 
earlier revisions of PW ASB No. 6039, and either (a) PW honeycomb third 
stage outer airseal Part Number (P/N) 801931, 802097, 797594, or 
798279; or (b) Pyromet Industries, Inc., honeycomb third stage outer 
airseal P/N PI9336; or (c) McClain International, Inc., honeycomb third 
stage outer airseal P/N M2433; or (d) a turbine case shield assembly 
installed in accordance with PW ASB No. 6039, Revision 2, dated May 4, 
1992, or earlier revisions of PW ASB No. 6039; or (e) a third stage 
blade set that has third stage turbine blades that were installed in 
accordance with PW SB No. 5331, dated October 27, 1982.
    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) by superseding AD 93-06-05 was published in the Federal 
Register on December 28, 1993 (58 FR 68572). That action proposed to 
continue to require repetitive inspections of installed third and 
fourth stage LPT blade sets for blade shroud crossnotch wear, and 
removal of blade sets found with excessively worn blade shroud 
crossnotches. These inspections are not required, however, for PW JT8D-
1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -17, and -17R engines 
that contain fan exhaust inner front duct segment assemblies that are 
installed in accordance with PW ASB No. 6039, Revision 3, dated October 
15, 1993, or earlier revisions of PW ASB No. 6039, and either (a) PW 
honeycomb third stage outer airseal P/N 801931, 802097, 797594, or 
798279; or (b) Pyromet Industries, Inc., honeycomb third stage outer 
airseal P/N PI9336; or (c) McClain International, Inc., honeycomb third 
stage outer airseal P/N M2433; or (d) a turbine case shield assembly 
installed in accordance with PW ASB No. 6039, Revision 3, dated October 
15, 1993, or earlier revisions of PW ASB No. 6039; or (e) a third stage 
blade set that has third stage turbine blades that were installed in 
accordance with PW SB No. 5331, dated October 27, 1982.
    That notice of proposed rulemaking (NPRM) also proposed to require, 
however, for all engines, installation of improved third stage LPT 
containment hardware at the next access to the third stage LPT air 
sealing ring, but not later than December 31, 1998; installation of the 
improved fourth stage LPT containment hardware at the next shop visit, 
but not later than December 31, 1998; installation of the improved No. 
6 bearing scavenge pump bracket bushing at the next shop visit, but not 
later than December 31, 1998; and modification and remarking with a new 
identification number third and fourth stage LPT vanes with a reduced 
platform leading edge dimension at the next shop visit, but not later 
than December 31, 1998. The installation of improved containment 
hardware would serve as terminating action for the repetitive 
inspections.
    The actions would be required to be accomplished in accordance with 
the following service documents: PW ASB No. A5913, Revision 6, dated 
October 15, 1993, that describes the third and fourth stage LPT blade 
set inspection procedures and replacement requirements; PW ASB No. 
A6110, Revision 1, dated October 15, 1993, that describes procedures 
for installation of improved LPT containment hardware; PW ASB No. 
A6131, dated August 24, 1993, that describes procedures for 
installation of an improved No. 6 bearing scavenge pump bracket 
bushing; and PW SB No. 5748, Revision 5, dated August 3, 1993, that 
describes procedures for removing material from the inner platform 
leading edge on third and fourth stage LPT vane and vane cluster 
assemblies, and remarking these modified vanes with new identification 
numbers.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    The FAA received several comments that state that inspections and 
modifications are available that address the root cause of shaft 
fractures and blade failures, whereas the installation of the 
containment hardware does not, and should therefore not be mandated. 
The FAA does not concur. Currently available inspections and 
modifications only protect against known failure modes, whereas the 
containment hardware will diminish the severity of all failure modes, 
both known and unknown, by protecting the aircraft from damage due to 
uncontained engine debris.
    The FAA received several comments that state that the FAA should 
evaluate PW JT8D engine models separately to determine if all models 
require the proposed actions to be accomplished, or if some models can 
be exempted from compliance due to differences in design or 
demonstrated operational safety. The FAA does not concur. Design 
differences between the various PW JT8D engine models were evaluated 
and no significant differences, other than low pressure rotor speed in 
the higher rated engines, were revealed that could impact containment 
capability. The increased rotor speeds are protected for in the design 
of the higher rated engines with the addition of a turbine shield, and 
the historical event data does not indicate that these higher low 
pressure rotor speeds result in a greater number of uncontained 
failures.
    One commenter states that the FAA's economic analysis does not 
reflect the true cost of the containment hardware. The FAA does not 
concur. The intent of the economic analysis is to quantify the total 
direct cost to operators of the proposed rule. The analysis does, 
however, account for engines currently equipped with the required 
parts, and the price for the required parts quoted in the proposed rule 
is actually an average value that reflects costs for these engines.
    One commenter states that the FAA's economic analysis does not 
account for the increased fuel costs resulting from the added weight of 
the containment hardware. The economic analysis reflects the direct 
costs of performing the requirements of the AD. Since the FAA has 
determined that the AD is required to correct an unsafe condition found 
in engines of this type design, and, therefore, operators must perform 
the requirements of the AD in order to ensure the continued 
airworthiness of the engines they operate, a comparison of the costs of 
operating the engine with and without the required containment hardware 
would not be proper.
    One commenter states that the definition of shop visit stated in 
the proposed rule encompasses many types of minor or peripheral 
maintenance activities where installation of the containment hardware 
cannot be accomplished, thus causing a forced induction into an 
overhaul facility. The FAA concurs. The shop visit definition has been 
revised to address this commenter's concern.
    One commenter states that the FAA's economic analysis should 
account for the costs to implement AD 93-06-05 and other safety 
concerns since they are directed at reducing the safety concern 
addressed by the proposed rule. AD 93-06-05 requires LPT blade torque 
check inspections. The FAA does not concur. The proposed rule maintains 
the inspection requirements of AD 93-06-05, but only until the 
installation of the containment hardware, which is ultimately required 
for all engines in accordance with the compliance schedule. Therefore, 
the inspections continue only as options, and only the mandated 
hardware installation is used to compute the direct costs of this AD. 
Further, since inspections are not mandated for engines that have 
containment hardware installed, only the cost of either the inspection 
or containment hardware applies for any given engine. The containment 
hardware cost, the higher of the two, was used on the assumption that 
an operator would install the hardware rather than continue with the 
optional inspection program.
    One commenter states that the modifications required by PW SB No. 
5748, LPT vane cluster cut-back, are not applicable to the engine 
models specified in this AD. This requirement should be eliminated from 
the AD. The FAA concurs. The modification of the LPT vane clusters in 
accordance with PW SB No. 5748, is not required for the ``non-A'' JT8D 
engine models and therefore has been eliminated from this AD.
    One commenter states that PMA 3rd stage outer air seal, Part Number 
(P/N) M2533, manufactured by McClain International, should be an 
acceptable alternative installation to the corresponding PW part, P/N 
811962. The FAA concurs. Third stage turbine outer air seal, P/N M2533, 
has been granted FAA PMA approval, and therefore meets all applicable 
Federal Aviation Regulations and is directly interchangeable with PW P/
N 811962. The AD has been revised to specify PP/N M2533 as an 
acceptable installation.
    One commenter states that a one-year extension of the compliance 
end date to December 31, 1999, should be granted. The FAA concurs. A 
one-year extension of the compliance end date has been granted to 
adjust for the time required to review the comments to the NPRM and 
process the Final Rule.
    One commenter states that only engines removed for shop visits on 
or after the AD effective date will be required to comply with the AD, 
and therefore AD compliance would not be required for engines already 
undergoing a shop visit as of the AD effective date. The FAA concurs, 
but no revision of the AD is required because the wording in the 
proposed rule accounts for this situation.
    One commenter states that the compliance requirements should be 
revised to minimize economic impact due to major engine disassembly. 
Specifically, modification of the LPT vane cluster assemblies and 
installation of the No. 6 bearing scavenge pump bracket bushing could 
entail major engine disassembly depending on the scope of work 
performed at the next shop visit occurring after the effective date of 
the AD. The FAA concurs in part. The FAA has determined that the 
modification of the LPT vane cluster assemblies is not applicable to 
the engine models specified in this AD, and therefore has eliminated 
this requirement. However, the compliance requirements for the 
installation of the No. 6 bearing scavenge pump bracket bushing is 
still required at the next shop visit to achieve the desired level of 
safety.
    One commenter states that additional costs could be incurred due to 
lack of availability of the parts required by this AD. The FAA does not 
concur. The FAA has coordinated this AD closely with PW to ensure the 
availability of the required parts. In addition, PMA parts are 
specified in this AD as an acceptable alternative for PW parts.
    One commenter states that the -15A/-17A models were the only engine 
group to have the initial steel duct modification incorporated during 
manufacture in accordance with PW SB No. 5697. These engines, together 
with a limited number of retrofitted engines, will be the only ones 
able to take advantage of the associated industry support program. The 
FAA has no comment on the extent or application of any support program 
which may offset some of the costs of the hardware required by this 
airworthiness directive. While some operators may receive discounts on 
the cost of the containment hardware, the economic analysis is computed 
on the assumption that no discount or warranty program is available. 
Therefore, this comment is beyond the scope of the AD or its economic 
analysis.
    One commenter states that an alternative to the compliance end date 
of December 31, 1998, should be expressed in hours and cycles, with 
performance required as whichever occur later, to accommodate low 
utilization operators. The FAA concurs. The FAA performed a risk 
analysis to determine the inspection interval requirements and that 
risk analysis accounted for both high and low utilization operations. 
However, determining the hourly and cyclic equivalent to the compliance 
end date specified in the AD, the FAA has determined that the fleet 
average utilization rate can be applied to low utilization operators. 
The FAA has added the hourly and cyclic equivalents to the AD.
    One commenter states the PW JT8D-17R engines should be exempted 
from the requirement to install the thicker third stage turbine outer 
air seal because these engines are already configured with a turbine 
shield for containment protection. The FAA does not concur. The PW 
JT8D-17R engines require additional containment protection due to 
higher rated low pressure rotor speeds on these engine models. 
Therefore, both the thicker third stage turbine outer air seal and the 
turbine shield are required for these engine models.
    One commenter concurs with the rule as proposed.
    In addition, the FAA has determined that inspections of the third 
and fourth stage LPT blade sets in accordance with the procedures and 
intervals described in PW ASB No. 5913, Revision 5, dated August 10, 
1992; or PW ASB No. 5913, Revision 4, dated February 20, 1992, 
constitute acceptable alternative methods of compliance for the 
inspections required by paragraphs (a)(1) and (a)(1)(iii) of this AD.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates that 6,000 engines installed on aircraft of U.S. 
registry will be affected by this AD, that it will take an average of 4 
work hours, based on fleet configuration mix, per engine to accomplish 
the required actions, and that the average labor rate is $55 per work 
hour. Required parts will cost approximately $7,235 per engine. Based 
on these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $44,730,000.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 39-8530 (58 FR 
31902, June 7, 1993) and by adding a new airworthiness directive, 
Amendment 39-9036, to read as follows:

94-20-08 Pratt & Whitney: Amendment 39-9036. Docket No. 93-ANE-83. 
Supersedes AD 93-06-05, Amendment 39-8530.

    Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -
7B, -9, -9A, -11, -15, -17, and -17R turbofan engines, installed on 
but not limited to Boeing 737 and 727 series aircraft, and McDonnell 
Douglas DC-9 series aircraft.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent damage to the aircraft resulting from engine debris 
following a low pressure turbine (LPT) blade or shaft failure, 
accomplish the following:
    (a) For engines that do not contain fan exhaust inner front duct 
segment assemblies that are installed in accordance with PW Alert 
Service Bulletin (ASB) No. 6039, Revision 3, dated October 15, 1993, 
or earlier revisions of PW ASB No. 6039, and either PW honeycomb 
third stage outer airseal Part Number (P/N) 801931, 802097, 797594, 
or 798279; or Pyromet Industries, Inc., honeycomb third stage outer 
airseal P/N PI9336; or McClain International, Inc., honeycomb third 
stage outer airseal P/N M2433; or a turbine case shield assembly 
installed in accordance with PW ASB No. 6039, Revision 3, dated 
October 15, 1993, or earlier revisions of PW ASB No. 6039; or a 
third stage blade set that has third stage turbine blades that were 
installed in accordance with PW SB No. 5331, dated October 27, 1982, 
accomplish the following:
    (1) Conduct initial and repetitive inspections on installed 
third and fourth stage LPT blade sets, and remove and replace with 
serviceable blade sets, as necessary, in accordance with Part 1 of 
the Accomplishment Instructions of PW ASB No. A5913, Revision 6, 
dated October 15, 1993; or PW ASB No. 5913, Revision 5, dated August 
10, 1992; or PW ASB No. 5913, Revision 4, dated February 20, 1992, 
as follows:
    (i) Initially inspect the blade shroud crossnotches of the third 
stage LPT blade set when specified in paragraphs (a)(1)(i)(A) or 
(a)(1)(i)(B) of this AD, whichever occurs later. Engines that 
contain a third stage blade set that have third stage turbine blades 
that were installed per the requirements specified in PW Service 
Bulletin No. 5331, dated October 27, 1982, do not require the third 
stage blade set inspection.
    (A) Inspect within 6,000 cycles or 6,000 hours time in service, 
whichever occurs first, since new, since the last blade shroud 
crossnotch inspection specified in Section 72-53-12 of PW JT8D 
Engine Manual P/N 481672, or since last blade shroud crossnotch 
repair that was accomplished per the requirements specified in 
Section 72-53-12 of PW JT8D Engine Manual P/N 481672; or
    (B) Inspect within 1,000 cycles or 1,000 hours time in service, 
whichever occurs first, after the effective date of this AD.
    (ii) Initially inspect the blade shroud crossnotches of the 
fourth stage LPT blade set when specified in paragraph (a)(1)(ii)(A) 
or (a)(1)(ii)(B) of this AD, whichever occurs later. Engines that 
contain fan exhaust inner front duct segment assemblies that were 
installed per the requirements of PW ASB No. 6039, Revision 3, dated 
October 15, 1993, or earlier revisions of PW ASB No. 6039, do not 
require the fourth stage blade set inspection.
    (A) Inspect within 6,000 cycles or 6,000 hours time in service, 
whichever occurs first, since new, since the last blade shroud 
crossnotch inspection specified in Section 72-53-13 of PW JT8D 
Engine Manual P/N 481672, or since last blade shroud crossnotch 
repair that was accomplished per the requirements specified in 
Section 72-53-13 of PW JT8D Engine Manual P/N 481672; or
    (B) Inspect within 1,000 cycles or 1,000 hours time in service, 
whichever occurs first, after the effective date of this AD.
    (iii) Thereafter, inspect the third and fourth stage LPT blade 
sets in accordance with the procedures and intervals specified in PW 
ASB No. A5913, Revision 6, dated October 15, 1993;
    (2) At the next shop visit after the effective date of this AD; 
but not later than December 31, 1999, 8,000 hours time in service 
after the effective date of this AD, or 7,000 cycles after the 
effective date of this AD, whichever occurs latest, install the 
improved inner front fan exhaust duct and associated hardware in 
accordance with Part A of the Accomplishment Instructions of PW ASB 
No. A6110, Revision 1, dated October 15, 1993.
    (3) At the next access to the third stage turbine air sealing 
ring after the effective date of this AD, but not later than 
December 31, 1999, 8,000 hours time in service after the effective 
date of this AD, or 7,000 cycles after the effective date of this 
AD, whichever occurs latest, install the improved third stage 
turbine air sealing ring and associated hardware in accordance with 
Part B of the Accomplishment Instructions of PW ASB No. A6110, 
Revision 1, dated October 15, 1993.

    Note: Third stage turbine outer air seal, P/N M2533, is an 
acceptable alternative to PW  P/N 811962 for compliance with this 
paragraph.

    (4) At the next shop visit after the effective date of this AD, 
but not later than December 31, 1999, 8,000 hours time in service 
after the effective date of this AD, or 7,000 cycles after the 
effective date of this AD, whichever occurs latest, install the 
improved No. 6 bearing scavenge pump bracket bushing in accordance 
with the Accomplishment Instructions of PW ASB No. A6131, dated 
August 24, 1993.
    (5) Accomplishment of the installations required by paragraphs 
(a)(2), (a)(3), and (a)(4) of this AD constitutes terminating action 
to the repetitive inspections required by paragraph (a)(1) of this 
AD.
    (b) For engines that do contain fan exhaust inner front duct 
segment assemblies that are installed in accordance with PW ASB No. 
6039, Revision 3, dated October 15, 1993, or earlier revisions of PW 
ASB No. 6039, and either PW honeycomb third stage outer airseal P/N 
801931, 802097, 797594, or 798279; or Pyromet Industries, Inc., 
honeycomb third stage outer airseal P/N PI9336; or McClain 
International, Inc., honeycomb third stage outer airseal P/N M2433; 
or a turbine case shield assembly installed in accordance with PW 
ASB No. 6039, Revision 3, dated October 15, 1993, or earlier 
revisions of PW ASB No. 6039; or a third stage blade set that has 
third stage turbine blades that were installed in accordance with PW 
SB No. 5331, dated October 27, 1982, perform the installations 
required by paragraphs (a)(2), (a)(3), and (a)(4) of this AD, at the 
times specified in those respective paragraphs.
    (c) For the purpose of this AD, a shop visit is defined as an 
engine removal, where engine maintenance entails separation of pairs 
of major mating engine flanges or the removal of a disk, hub, or 
spool at a maintenance facility that is capable of compliance with 
the instructions of this AD, regardless of other planned 
maintenance, except for field maintenance type activities performed 
at this maintenance facility in lieu of performing them on-wing or 
at another peripheral facility.
    (d) 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 method of compliance with this AD, if any, may be 
obtained from the Engine Certification Office.

    (e) 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.
    (f) The installations shall be done in accordance with the 
following service documents:

------------------------------------------------------------------------
      Document No.         Pages     Revision              Date         
------------------------------------------------------------------------
PW ASB No. A5913........     1     6...........  October 15, 1993.      
                             2     4...........  February 20, 1992.     
                           3-8     6...........  October 15, 1993.      
                             9     4...........  February 20, 1992.     
                            10     6...........  October 15, 1993.      
                            11     4...........  February 20, 1992.     
                            12     6...........  October 15, 1993.      
Appendix A..............     1     6...........  October 15, 1993.      
                           2-3     5...........  August 10, 1992.       
                             4     2...........  September 28, 1990.    
                             5     6...........  October 15, 1993.      
                             6     Original....  April 2, 1990.         
                             7     2...........  September 28, 1990.    
                          8-14     Original....  April 2, 1990.         
Total pages: 26.                                                        
PW ASB No. A6110........     1     1...........  October 15, 1993.      
                             2     Original....  March 19, 1993.        
                          3-59     1...........  October 15, 1993.      
Total pages: 59.                                                        
PW ASB No. A6131........  1-13     Original....  August 24, 1993.       
Total pages: 13.                                                        
------------------------------------------------------------------------

    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 
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.
    (g) This amendment becomes effective on November 14, 1994.

    Issued in Burlington, Massachusetts, on September 22, 1994.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 94-24200 Filed 10-12-94; 8:45 am]
BILLING CODE 4910-13-P