[Federal Register Volume 64, Number 77 (Thursday, April 22, 1999)]
[Proposed Rules]
[Pages 19726-19728]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10054]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 64, No. 77 / Thursday, April 22, 1999 /
Proposed Rules
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-22-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW4000 Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Pratt & Whitney (PW) PW4000 series
turbofan engines. This proposal would establish short term criteria for
limiting the number of engines with potentially reduced stability on
each airplane to no more than one engine, would require initial and
repetitive on-wing or test cell cold takeoff high pressure compressor
(HPC) stability tests, would require removal of engines from service
that fail on-wing test acceptance criteria, and would allow a follow-on
test cell stability test. The AD also establishes required intervals
for stability testing of the remaining engine with potentially reduced
stability on the airplane and requirements for reporting test data.
This proposal is prompted by a report of a dual-engine HPC surge event
and reports of single-engine HPC surge events during the takeoff and
climb phases of flight. The actions specified by the proposed AD are
intended to prevent an HPC surge event, which could result in engine
power loss at a critical phase of flight such as takeoff or climb.
DATES: Comments must be received by May 24, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 99-NE-22-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ad-
[email protected].'' Comments sent via the Internet must contain the
docket number in the subject line. Comments may be inspected at this
location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
telephone (860) 565-6600, fax (860) 565-4503. This information may be
examined at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Peter White, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7128, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal 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 99-NE-22-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRM's
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-NE-22-AD, 12 New England Executive Park,
Burlington, MA 01803-5299.
Discussion
The Federal Aviation Administration (FAA) has received a report of
a dual-engine high pressure compressor (HPC) surge event and several
reports of single-engine HPC surge events on Pratt & Whitney (PW)
PW4000 series turbofan engines. The FAA has determined that these HPC
surges are caused by excessive HPC blade tip-to-stator assembly
clearances in the aft stages of the HPC. The average maximum clearance
between the blade tip and the stator assembly is reached during a cold
engine takeoff approximately 60 seconds after throttle advance from
idle to takeoff power, as a result of different thermal growth rates of
the HPC rotor and stator components. The manufacturer's data indicates
that some PW4000 engines exhibit reduced stability resulting from
clearances larger than those due to this thermal mismatch alone.
Testing has indicated that binding of stator assembly segments in the
HPC outer casing can result in flow path distortion and produce local
open clearances. These two factors (average maximum clearance and local
open clearances) combine to produce excessive local blade tip-to-stator
assembly clearances, which reduce stability and create subsequent
engine surge.
The FAA has issued AD 98-23-08, Amendment 39-10873, (63 FR 63391,
November 13, 1998) which was intended to reduce the rate of single-
engine surges. Although the surge rates for engines that have
incorporated the requirements of that AD have been reduced, the FAA has
determined that further improvement is necessary. The investigation of
engine surge events has determined that the dual-engine HPC surge event
and several single-engine surge events have occurred on engines that
meet the requirements of AD 98-23-08.
[[Page 19727]]
This condition, if not corrected, could result in an HPC surge
event, which could result in engine power loss at a critical phase of
flight such as takeoff or climb.
The FAA has reviewed and approved the technical contents of PW
Special Instructions (SI) 49F96, dated August 9, 1996, PW SI 7F-96,
dated January 10, 1996, and PW PW4000 Engine Manual Temporary Revisions
71-0016, 71-0025, and 71-0030, all dated March 15, 1999, and PW SI 32F-
99, dated March April 13, 1999, which describe procedures for assessing
the stability of PW4000 engines. Since an unsafe condition has been
identified that is likely to exist or develop on other Pratt & Whitney
(PW) PW4000 series turbofan engines of the same type design, the
proposed AD would require short term criteria for limiting the number
of engines with potentially reduced stability on each airplane to no
more than one engine, would require initial and repetitive on-wing or
test cell cold takeoff high pressure compressor (HPC) stability tests
for all affected PW4000 series engines, would require removal from
service of engines that fail on-wing test criteria, and would allow a
follow-on test-cell stability test. Initial on-wing testing is required
to limit the number of engines on the aircraft to no more than one
engine that has exceeded the initial stability threshold. The proposed
AD also establishes requirements to perform a stability test of the
remaining engine with potentially reduced stability on the airplane.
The stability tests are required to be accomplished in accordance with
the special instructions described previously. This proposed AD has
been drafted in conjunction with the Transport Aircraft Directorate, to
coordinate the aircraft level aspects of this compliance plan. Data
reporting requirements are necessary for this AD to allow continuous
monitoring of the effectiveness and assumptions of this compliance
plan. The manufacturer does not receive data on all of the tests that
are performed, and this data is necessary to continuously monitor this
plan. Additional rulemaking may be necessary based on the results of
the data collected.
There are approximately 2,200 engines of the affected design in the
worldwide fleet. The FAA estimates that 546 engines installed on
aircraft of U.S. registry would be affected by this proposed AD. The
FAA also estimates that, on average, approximately 192 on-wing tests,
60 test cell stability tests, 11 engine removals, and 19 HPC overhauls
will be required annually. It is estimated that the cost to industry of
an on-wing stability test will average $2,000, a test cell stability
test will average $12,000, an engine removal is approximately $5,000,
and an HPC overhaul will cost approximately $400,000. Based on these
figures, the total average annual cost impact of the proposed AD to
U.S. operators is estimated to be $8,759,000.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Pratt & Whitney: Docket No. 99-NE-22-AD.
Applicability: Pratt & Whitney PW4050, PW4052, PW4056, PW4060,
PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160,
PW4460, PW4462 and PW4650 turbofan engines installed on, but not
limited to certain models of Boeing 747, Boeing 767, Airbus
Industrie A300, Airbus Industrie A310, and McDonnell Douglas MD-11
series airplanes.
Note 1: 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 request
approval for an alternative method of compliance in accordance with
paragraph (h) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent a high pressure compressor (HPC) surge event, which
could result in engine power loss at a critical phase of flight such
as takeoff or climb, accomplish the following:
(a) Limit the number of engines on each airplane to no more than
one untested engine that has exceeded the initial threshold
specified in Table 1 of this AD, within 1,000 engine cycles in
service (CIS) from the effective date of this AD or by December 31,
1999, whichever comes first, by one of the following methods:
(1) Conduct an initial on-wing stability test on engines listed
in Table 1 of this AD, which have accumulated cycles equal to or
greater than the associated initial threshold listed in Table 1 of
this AD, as follows:
(i) Perform either a Cool Bodie stability test in accordance
with PW Special Instructions 7F-96,dated January 10, 1996. Refer to
Table 2 of this AD for disposition instructions, or;
(ii) Perform an E1E stability test in accordance with paragraphs
A through D and F through H of the Run On-Wing E1E Testing section
of PW Special Instructions 49F-96, dated August 9, 1996. Refer to
Table 2 of this AD for disposition instructions.
(iii) For purposes of this AD, the initial threshold for PW4056,
PW4156, and PW4156A, first run, full-up engines, applies only to
engines that have incorporated service bulletins PW4ENG 72-474, 72-
477, 72-484, 72-575, 72-485, 72-486, and 72-514 at original
manufacture, and have had no work performed on the HPC and high
pressure turbine gas path.
(2) Remove from service those engines listed in Table 1 of this
AD with HPC's that have accumulated cycles equal to or greater than
the initial threshold listed in Table 1 of this AD and replace with
a serviceable engine that has undergone applicable initial and
repetitive testing in accordance with paragraphs (a), (b) and (c) of
this AD.
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Table 1
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Models Initial threshold Engine manual
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PW4052, PW4152, PW4158, PW4050, PW4650.. 2400 HPC cycles since new 50A605, 50A443
or since HPC overhaul.
PW4056,* PW4156,* PW4156A *............. 1700 engine cycles since 50A605, 50A443
new.
PW4056, PW4156, PW4156A................. 1200 HPC cycles since HPC 50A605, 50A443
overhaul.
PW4060, PW4060A, PW4060C, PW4062, 1200 HPC cycles since new 50A605, 50A443,50A822
PW4160, PW4460, PW4462. or since HPC overhaul.
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First Run, Full Up Engines.
Table 2.--On-Wing Acceptance Criteria
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Test type Test result Disposition
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Cool Bodie: In accordance with SI 7F-96, Pass....................... Continue in service.
dated August 9, 1996.
Failure.................... Remove from service or conduct E1E. If
<0.02 continue in service. If E1E is 0.02 remove from service, prior
to further flight.
E1E: In accordance with SI 49F-96, dated <0.02...................... Continue in service.
January 10, 1996.
0.02 but 0.032. service. If fail remove engine from
service, prior to further flight.
>0.032..................... Remove from service, prior to further
flight.
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(b) For engines removed from service in accordance with
paragraph (a) of this AD, a cold engine fuel spike stability test
(Testing--20) may be done in accordance with the associated PW
PW4000 Engine Manual Temporary Revisions 71-0016, 71-0025, and 71-
0030, all dated March 15, 1999, or PW SI 32F-99, dated April 13,
1999. Engines that pass a test cell stability test may be returned
to service.
(c) Repeat stability tests in accordance with paragraph
(a)(1)(i) or (a)(1)(ii) on engines that meet the acceptance criteria
of Table 2 of this AD or pass a test cell stability test in
accordance with paragraph (b) before accumulating 800 CIS since last
stability test.
(d) Remove from service engines that do not meet the acceptance
criteria of Table 2, prior to further flight and replace with a
serviceable engine that has undergone applicable initial and
repetetive testing in accordance with paragraphs (a), (b) and (c) of
this AD.
(e) Conduct stability tests on the remaining engine on each
airplane before accumulating 1800 engine CIS after the effective
date of this AD, or by December 31, 2000, whichever comes first, in
accordance with paragraph (a) of this AD.
(f) Engines that have not reached the initial threshold
specified in Table 1 of this by 1000 engine CIS after the effective
date of this AD, or by December 31, 1999, whichever comes first,
must be tested before the engine reaches the initial threshold so
that no more than one engine per airplane has not been tested. After
accumulating 1800 CIS or December 31, 2000, whichever comes first,
the engines must be managed so that all engines have been tested in
accordance with the initial thresholds specified in Table 1 of this
AD or the repetitive 800 CIS threshold requirement of this AD.
(g) After the effective date of this AD, a cold engine fuel
spike stability test (Testing--20) must be performed in accordance
with PW Temporary Revision 71-0016, 71-0025, or 71-0030, all dated
March 15, 1999, or PW SI 32F-99, dated April 13, 1999, before an
engine can be returned to service after having undergone maintenance
in the shop, except under any of the following conditions:
(1) The HPC stage 12 through 14 blade tip clearances were
restored to the clearances specified in the applicable fits and
clearances engine manual during the shop visit, or the HPC was
replaced with a new HPC during the shop visit.
(2) Less than 800 CIS have passed since the last accomplishment
of Testing--20, unless a major engine flange was separated during
the shop visit.
(3) The shop visit was only for replacement of a line
replaceable unit, with no other work done, unless a major engine
flange was separated during the shop visit.
Note 2: Boeing SB 767-72A0034, dated April 16, 1999, and SB 747-
72A2038, dated April 16, 1999, include instructions similar to those
contained in this AD, however, these SB's are not approved as
alternate methods of compliance with this AD.
(h) 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.
Operators shall submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(i) Report the results of the stability assessment tests to the
Manager, Engine Certification Office, 12 New England Executive Park,
Burlington, MA 01803-5299. Data to be reported includes engine
serial number, type and date of the test, results of the test
(include E1E value if applicable), position of engine on the
airplane, disposition of the engine after the test, time and cycles
since compressor overhaul, and total time on engine and total cycles
at the time of the test. Reporting requirements have been approved
by the Office of Management and Budget (OMB) and assigned OMB
control number 2120-0056.
(j) Special flight permits may be issued in accordance
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.
Issued in Burlington, Massachusetts, on April 14, 1999.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-10054 Filed 4-21-99; 8:45 am]
BILLING CODE 4910-13-P