AD 2001-15-12
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Pratt | PW4000 | Airworthiness Directives; Pratt and Whitney PW4000 Series Turbofan Engines |
Unsafe Condition
High pressure compressor (HPC) surges in Pratt and Whitney PW4000 series turbofan engines, particularly those with the HPC in the cutback stator (CBS) configuration, leading to multiple-engine power losses and increased single-engine surge events.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Limit the number of engines with the HPC CBS configuration to one on each airplane within 100 cycles-in-service (CIS) after the effective date. Limit the number of PW4000 engines with potentially reduced stability on each airplane, based on configuration, within 50 CIS after the effective date. Remove certain PW4000 engines from service before exceeding cyclic limits on the HPC based on cycles-since-overhaul (CSO), within 50 CIS after the effective date. Prevent the build-up of engines with an HPC having 1,500 or more CSO greater than the high pressure turbine (HPT) CSO. Establish a minimum rebuild standard for engines returned to service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 or 100 cycles-in-service (CIS) after the effective date, depending on the specific action.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pratt and Whitney PW4000 series turbofan engines, specifically those with the HPC in the CBS configuration and those with potentially reduced stability, as defined by the AD. Affected airplane models include Boeing 747, Boeing 767, and McDonnell Douglas MD-11 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This amendment supersedes two airworthiness directives (AD's), 2000-22-01 and 2001-09-07, that both apply to Pratt and Whitney (PW) model PW4000 series turbofan engines. AD 2000-22-01 requires that operators limit the number of PW4000 engines equipped with the high pressure compressors (HPC) in the cutback stator (CBS) configuration to no more than one engine on each airplane, and prohibits the installation of engines with HPC modules in the CBS configuration after the effective date of that AD. AD 2001-09-07 requires that operators limit the number of engines with potentially reduced stability to no more than one engine on each airplane, and remove those engines before exceeding certain cyclic limits. Reports of HPC surges in PW4000 engines that have the HPC in the CBS configuration prompted those AD's. This Amendment will limit the number of PW4000 engines with potentially reduced stability on each airplane by applying rules based on airplane and engine configuration, and require that engines that exceed HPC compressor cyclic limits based on cycles-since-overhaul (CSO) are removed from service. This AD will also limit the number of engines with HPC CBS configuration to one on each airplane, and will establish a minimum rebuild standard for engines that are returned to service. This Amendment is prompted by further analyses of compressor surges in PW4000 engines. The actions specified by this AD are intended to prevent multiple-engine power losses due to high pressure compressor (HPC) surge and to reduce the rate of single-engine surge events.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 66, Number 144 (Thursday, July 26, 2001)]
[Rules and Regulations]
[Pages 38896-38902]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-18432]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-47-AD; Amendment 39-12346; AD 2001-15-12]
RIN 2120-AA64
Airworthiness Directives; Pratt and Whitney PW4000 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule, request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes two airworthiness directives (AD's),
2000-22-01 and 2001-09-07, that both apply to Pratt and Whitney (PW)
model PW4000 series turbofan engines. AD 2000-22-01 requires that
operators limit the number of PW4000 engines equipped with the high
pressure compressors (HPC) in the cutback stator (CBS) configuration to
no more than one engine on each airplane, and prohibits the
installation of engines with HPC modules in the CBS configuration after
the effective date of that AD. AD 2001-09-07 requires that operators
limit the number of engines with potentially reduced stability to no
more than one engine on each airplane, and remove those engines before
exceeding certain cyclic limits. Reports of HPC surges in PW4000
engines that have the HPC in the CBS configuration prompted those AD's.
This Amendment will limit the number of PW4000 engines with
potentially reduced stability on each airplane by applying rules based
on airplane and engine configuration, and require that engines that
exceed HPC compressor cyclic limits based on cycles-since-overhaul
(CSO) are removed from service. This AD will also limit the number of
engines with HPC CBS configuration to one on each airplane, and will
establish a minimum rebuild standard for engines that are returned to
service. This Amendment is prompted by further analyses of compressor
surges in PW4000 engines. The actions specified by this AD are intended
to prevent multiple-engine power losses due to high pressure compressor
(HPC) surge and to reduce the rate of single-engine surge events.
DATES: Effective August 10, 2001.
Comments for inclusion in the Rules Docket must be received on or
before September 24, 2001.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 2000-NE-47-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#20190d414e450d4144434f4d4d454e54604641410e474f56"><span class="__cf_email__" data-cfemail="8fb6a2eee1eaa2eeebece0e2e2eae1fbcfe9eeeea1e8e0f9">[email protected]</span></a>.'' Comments sent via the Internet must contain the
docket number in the subject line.
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: The FAA has noted a growing number of take-
off (T/O) surge events in Pratt and Whitney PW4000 Series turbofan
engines. These surges typically occur within 60 seconds after throttle
advance to T/O power, a critical phase of flight. These events have
resulted in numerous aborted T/O's, in-flight engine shutdowns, and
diverted flights. A surge of this kind on a single engine of a multi-
engine airplane would not normally result in an unsafe condition. To
date, two dual-engine surge events have occurred, the latest in March
2001 involving a twin-engine aircraft.
The investigation into these events has revealed no special causes
for these surges. The FAA believes that a low-stall margin results from
open clearances in the aft stages of the HPC. The worst-case open
clearance
[[Page 38897]]
condition in the aft stage compressor of the HPC occurs about 60
seconds after the throttle is advanced for T/O. A binding of the
compressor flowpath and stator segments within the outer case (causing
out-of-round flowpath or local open clearances) adds to this normally
worst-case condition. Pratt and Whitney has initiated a root-cause
analysis program to verify this belief, and to identify other
contributing factors that may contribute to the high rate of takeoff
surges in the PW4000 fleet.
On October 25, 2000, the FAA issued AD 2000-22-01 (65 FR 63793,
dated October 25, 2000), applicable to PW4000 series engines, to
require limiting the number of engines with the HPC CBS configuration,
which are used on Boeing 747, Boeing 767, and McDonnell Douglas MD-11
series airplanes, to one on each airplane according to the cyclic
limits specified in that AD. AD 2000-22-01 also prohibits using engines
with HPC modules that incorporated the HPC CBS configuration, after the
effective date of that AD.
On April 20, 2001, the FAA issued AD 2001-09-07 (66 FR 21083, dated
April 27, 2001), applicable to PW4000 series turbofan engines, to
require limiting the number of PW4000 engines to no more than one
engine with potentially reduced stability on each airplane and removal
of certain PW4000 engines before exceeding cyclic limits that are
determined by airplane model. Those engines with potentially reduced
stability are listed by serial number in the AD. AD 2001-09-07
superseded emergency AD 2001-08-52. AD 2001-09-07 also requires the
removal of certain PW4000 engines that have an HPC with 1,500 or more
CSO greater than the high pressure turbine (HPT) CSO, and establishes a
minimum rebuild standard for engines that are returned to service.
Since AD 2000-22-01 and AD 2001-09-07 were issued, the FAA has
reevaluated those requirements and found that the requirements of those
AD's were not sufficient to meet the original safety intent of those
AD's. The PW4000 fleet was evaluated by configuration, installation,
thrust rating and other variables to determine which subpopulations are
most prone to high power takeoff surges. This information was then
evaluated to create cyclic limits for each airplane and engine
combination to maintain the risk of a multiple-engine dual surge risk
at an acceptable level. Cyclic limits were then developed for the HPC
to reduce the single engine surge rate.
FAA's Determination of an Unsafe Condition and Proposed Actions
Since the unsafe condition described is likely to exist or develop
on other PW4000 series turbofan engines of the same type design, this
AD is being issued to prevent multiple-engine power losses due to HPC
surge and to reduce the rate of single-engine surge events. This AD
requires:
<bullet> Limiting the number of engines with the HPC CBS
configuration to one on each airplane within 100 cycles-in-service
(CIS) after the effective date of this AD, AND
<bullet> Limiting the number of PW4000 engines with potentially
reduced stability on each airplane, based upon airplane and engine
configuration, within 50 CIS after the effective date of this AD, AND
<bullet> Removing certain PW4000 engines from service, before
exceeding cyclic limits on the HPC based on CSO, within 50 CIS after
the effective date of this AD, AND
<bullet> Preventing the build-up of PW4000 engines that have an HPC
with 1,500 or more CSO greater than the HPT CSO, AND
<bullet> A minimum rebuild standard for engines that are returned
to service.
Interim Action
The actions specified in this AD are considered interim action and
further action is anticipated based on the continuing investigation of
the HPC surges. This AD has been coordinated with the FAA Transport
Aircraft Directorate.
Immediate Adoption of This AD
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 2000-NE-47-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
This final rule does not have federalism implications, as defined
in Executive Order 13132, because it would not have a substantial
direct effect 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. Accordingly,
the FAA has not consulted with state authorities prior to publication
of this final rule.
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, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
[[Page 38898]]
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-11947 (65 FR
63793, dated October 25, 2000) and Amendment 39-12212 (66 FR 21083,
dated April 27, 2001), and by adding a new airworthiness directive
(AD), Amendment 39-12346, to read as follows:
2001-15-12 Pratt and Whitney: Amendment 39-12346. Docket No. 2000-
NE-47-AD. Supersedes Amendment 39-11947, and Amendment 39-12212.
Applicability: This airworthiness directive (AD) is applicable
to Pratt and Whitney (PW) model PW4050, PW4052, PW4056, PW4060,
PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160,
PW4460, PW4462, and PW4650 turbofan engines. These engines are
installed on, but not limited to, certain models of Airbus Industrie
A300, Airbus Industrie A310, Boeing 747, Boeing 767, and McDonnell
Douglas MD-11 series airplanes.
Note 1: This 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 (l) 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: Compliance with this AD is required as indicated,
unless already done.
To prevent multiple-engine power losses due to high pressure
compressor (HPC) surge and to reduce the rate of single-engine surge
events, do the following:
(a) When complying with this AD, use the following Table 1 of
this AD to determine the configuration of each engine on each
airplane:
Table 1.--Engine Configuration Listing
----------------------------------------------------------------------------------------------------------------
Configuration Configuration designator Description
----------------------------------------------------------------------------------------------------------------
(1) Phase 1 without high pressure turbine A Engines that did not incorporate
(HPT) 1st turbine vane cut back (1TVCB). the Phase 3 configuration at
the time they were originally
manufactured, or have not been
converted to Phase 3
configuration; and have not
incorporated HPT 1TVCB using
any revision of SB PW4ENG 72-
514.
----------------------------------------------------------------------------------------------------------------
(2) Phase 1 with 1TVCB. B Same as configuration (1) except
that HPT 1TVCB has been
incorporated using any revision
of SB PW4ENG 72-514.
----------------------------------------------------------------------------------------------------------------
(3) Phase 3, 2nd Run. B Engines that incorporated the
Phase 3 configuration at the
time they were originally
manufactured, or have been
converted to the Phase 3
configuration during service;
and that have had at least one
HPC overhaul since new.
----------------------------------------------------------------------------------------------------------------
(4) Phase 3, 1st Run. C Same as configuration (3) except
that that the engine has not
had an HPC overhaul since new.
----------------------------------------------------------------------------------------------------------------
(5) HPC Cutback Stator Configuration D Engines that incorporated any
Engines. revision of SB's PW4ENG72-706,
PW4ENG72-704, or PW4ENG72-711.
----------------------------------------------------------------------------------------------------------------
(b) Within 50 cycles-in-service (CIS) after the effective date
of this AD, and thereafter, remove engines from service that exceed
the HPC cycles-since-new (CSN) or cycles-since-overhaul (CSO) limits
in the following Table 2 of this AD:
Table 2.--HPC Cyclic Limits by Engine Configuration
----------------------------------------------------------------------------------------------------------------
Engine configuration (CSO or CSN)
Engine model Engine serial number (SN) ------------------------------------------
A B C D
----------------------------------------------------------------------------------------------------------------
(1) PW4152 All 3,600 5,600 8,000 1,300
----------------------------------------------------------------------------------------------------------------
[[Page 38899]]
(2) PW4156, PW4156A, and 717205, 717702, 717703, 717710, 3,200 4,400 8,000 1,300
PW4158. 717752, 717788, 717798, 717799,
724023, 724026, 724027, 724033,
724034, 724036, 724037, 724040,
724041, 724044, 724045, 724048,
724049, 724050, 724052, 724055,
724056, 724059, 724061, 724062,
724063, 724065, 724067, 724073,
724074, 724075, 724079, 724094,
724095, 724551, 724552, 724555,
724556, 724557, 724558, 724561,
724562, 724563, 724564, 724567,
724568, 724569, 724570, 724571,
724572, 724573, 724574, 724575,
724576, 724578, 724640, 724806,
724807, 724808, 724809, 724811,
724820, 724821, 724827, 724833,
724835, 724836, 724840, 724841,
724848, 724849, 724855, 724857,
724858, 724861, 724862, 724865,
724866, 724868, 724909, 724910,
724913, 724914, 724924, 724925,
724926, 724927, 727912, 728519,
728520, 728521, 728522, 728523,
728524, 728525, 728526, 728527,
728528, 728534, 728535, 728536,
728537, 728538, 728539, 728540,
728541, 728542, 728543, 728544,
728545, 728546, 728547, 728548,
728549, 728550, 728551, 728552,
728553, 728554, 728557, 728558,
728559, 728560, 728561, 728562,
728563, 728564
----------------------------------------------------------------------------------------------------------------
(3) PW4158. 717704, 724001, 724002, 724004, 6,500 7,500 8,000 1,300
724005, 724006, 724007, 724008,
724009, 724010, 724011, 724019,
724020, 724031, 724035, 724038,
724039, 724042, 724043, 724047,
724068, 724069, 724071, 724076,
724077, 724080, 724085, 724086,
724087, 724092, 724093, 724096,
724097, 724801, 724802, 724803,
724804, 724805, 724813, 724814,
724819, 724823, 724824, 724825,
724826, 724828, 724831, 724832,
724843, 724846, 724847, 724851,
724852, 724853, 724854, 724859,
724860, 724863, 724864, 724867,
724869, 724870, 724871, 724872,
724873, 724874, 724875, 724876,
724880, 724881, 724882, 724883,
724884, 724885, 724886, 724887,
724888, 724889, 724890, 724892,
724893, 724894, 724895, 724896,
724897, 724898, 724899, 724900,
724932, 727315, 727436, 728501,
728502, 728503, 728504, 728505,
728506, 728507, 728508, 728509,
728510, 728511, 728515, 728518,
728531, 728532, 728533
----------------------------------------------------------------------------------------------------------------
(4) PW4156, PW4156A, and All others not listed by SN in this 2,150 2,800 8,000 1,300
PW4158. Table.
----------------------------------------------------------------------------------------------------------------
(5) PW4052 and 4056. All engines. 3,000 4,400 4,400 1,300
----------------------------------------------------------------------------------------------------------------
(6) PW4060, PW4060C, PW4062, All engines. 2,150 3,600 4,400 1,300
PW4460, and PW4462.
----------------------------------------------------------------------------------------------------------------
Engines Installed on Boeing 747 Airplanes
(c) Within 50 CIS after the effective date of this AD, and
thereafter, for engines installed on Boeing 747 series aircraft,
configure the airplane so that all of the following rules are met:
(1) At least one engine must be below the cyclic limits listed
under Rule 1a in the following Table 3 of this AD:
Table 3.--HPC CSO or CSN Cyclic Limits by Engine Configuration for Boeing 747 Airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Number of engines in each Configuration on the Airplane Rule 1a Rule 1b Rule 1c Rule 1d (Quantity of engines in each
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ configuration)
--------------------------------------------------
A B or C D A B or C D A B or C D A B or C D A B or C D
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(i) 4 0 0 700 ................ ................ 1300 ............... ............... 1800 ............... ............... (1)--2400 ............... ...............
(3)--400.......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(ii) 3 1 0 700 2300 ................ 1300 2600 ............... 1800 3000 ............... (1)--2400 (1)--1800 ...............
(2)--400.......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 38900]]
(iii) 2 2 0 700 2300 ................ 1300 2600 ............... 1800 3000 ............... (1)--2400 (2)--1800 ...............
(1)--400.......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(iv) 1 3 0 700 2300 ................ 1300 2600 ............... 1800 3000 ............... (1)--2400 (3)--1800 ...............
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(v) 0 4 0 ................ 2300 ................ ............... 2600 ............... ............... 3000 ............... ............... (1)--3300 ...............
(3)--1800......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(vi) 3 0 1 700 ................ 750 1300 ............... 750 1800 ............... 750 (1)--2400 ............... (1)--750.
(2)--400.......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(vii) 2 1 1 700 2300 750 1300 2600 750 1800 3000 750 (1)--2400 (1)--1800 (1)--750.
(1)--400.......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(viii) 1 2 1 700 2300 750 1300 2600 750 1800 3000 750 (1)--2400 (2)--1800 (1)--750.
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(ix) 0 3 1 ................ 2300 750 ............... 2600 750 ............... 3000 750 ............... (1)--3300 (1)--750.
(2)--1800......
--------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(2) At least two engines must be below the cyclic limits listed
under Rule 1b in Table 3 of this AD.
(3) At least three engines must be below the cyclic limits
listed under Rule 1c in Table 3 of this AD.
(4) At least one engine must be below the cyclic limits listed
under Rule 1d in Table 3 of this AD. When applying Rule 1d of this
AD, and two limits are shown for an engine configuration, the higher
cyclic limit for that configuration must be applied only to the
engine with the highest CSO or CSN of that configuration. The lower
limit is then applied to the remaining engines of that
configuration.
Engines Installed on McDonnell Douglas MD-11 Airplanes
(d) Within 50 CIS after the effective date of this AD, and
thereafter, for engines installed on McDonnell Douglas MD-11
airplanes, configure the airplane so that all of the following rules
are met:
(1) At least one engine must be below the cyclic limits listed
under Rule 2a in the following Table 4 of this AD:
Table 4.--HPC CSO or CSN Cyclic Limits by Engine Configuration for McDonnell Douglas MD-11
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Number of engines in each Configuration the Airplane Rule 2a Rule 2b Rule 2c (Quantity of Engines in each Configuration)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
A B C D A B C D A B C D A B C D
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(i) 3 0 0 0 850 ................. ................. ................. 1000 ................. ................. ................. (1)--1600 ................ ................ ................
(2)--600.........
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(ii) 2 1 0 0 850 1700 ................. ................. 1000 2300 ................. ................. (1)--1600 (1)--1400 ................ ................
(1)--600.........
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(iii) 1 2 0 0 850 1700 ................. ................. 1000 2300 ................. ................. (1)--1600 (2)--1400 ................ ................
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(iv) 0 3 0 0 ................. 1700 ................. ................. ................. 2300 ................. ................. ................. (1)--3000 ................ ................
(2)--1400.......
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(v) 2 0 1 0 850 ................. 2650 ................. 1000 ................. 2900 ................. (1)--1600 ................ (1)--2800 ................
(1)--600.........
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(vi) 1 0 2 0 850 ................. 2650 ................. 1000 ................. 2900 ................. (1)--1600 ................ (2)--2800 ................
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(vii) 0 0 3 0 ................. ................. 2650 ................. ................. ................. 2900 ................. ................. ................ (1)--3200 ................
(2)--2800.......
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(viii) 2 0 0 1 850 ................. ................. 750 1000 ................. ................. 750 (1)--1600 ................ ................ (1)--750.
(1)--600.........
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(ix) 0 2 1 0 ................. 1700 2650 ................. ................. 2300 2900 ................. ................. (1)--3000 (1)--2800 ................
(1)--1400.......
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(x) 0 1 2 0 ................. 1700 2650 ................. ................. 2300 2900 ................. ................. (1)--3000 (2)--2800 ................
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(xi) 0 2 0 1 ................. 1700 ................. 750 ................. 2300 ................. 750 ................. (1)--3000 ................ (1)--750.
(1)--1400.......
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(xii) 0 0 2 1 ................. ................. 2650 750 ................. ................. 2900 750 ................. ................ (1)--3200 (1)--750.
(1)--2800.......
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(xiii) 1 1 1 0 850 1700 2650 ................. 1000 2300 2900 ................. (1)--1600 (1)--1400 (1)--2800 ................
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(xiv) 1 1 0 1 850 1700 ................. 750 1000 2300 ................. 750 (1)--1600 (1)--1400 ................ (1)--750.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 38901]]
(xv) 1 0 1 1 850 ................. 2650 750 1000 ................. 2900 750 (1)--1600 ................ (1)--2800 (1)--750.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(xvi) 0 1 1 1 ................. 1700 2650 750 ................. 2300 2900 750 ................. (1)--3000 (1)--2800 (1)--750.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(2) At least two engines must be below the cyclic limits listed
under Rule 2b in Table 4 of this AD.
(3) At least one engine must be below the cyclic limits listed
under Rule 2c in Table 4 of this AD. When applying Rule 2c of this
AD, and two limits are shown for an engine configuration, the higher
cyclic limit for that configuration must be applied only to the
engine with the highest CSO or CSN of that configuration. The lower
limit is then applied to the remaining engines of that
configuration.
Engines Installed on Boeing 767, Airbus A300, or Airbus A310 Airplanes
(e) Within 50 CIS after the effective date of this AD, and
thereafter, for engines installed on Boeing 767 Series, Airbus A300
series or Airbus A310 series airplanes, configure the airplane so
that no more than one engine may exceed the cyclic limits listed in
the following Table 5 of this AD:
Table 5.--HPC CSO or CSN Cyclic Limits by Engine Configuration for Twin-Engine Airplane
----------------------------------------------------------------------------------------------------------------
Engine configuration (CSO or CSN)
Engine model Engine serial number (SN) ------------------------------------------
A B C D
----------------------------------------------------------------------------------------------------------------
(1) PW4152. All 2,500 4,000 6,600 750
----------------------------------------------------------------------------------------------------------------
(2) PW4156, PW4156A, and 717205, 717702, 717703, 717710, 2,000 3,200 6,600 750
PW4158. 717752, 717788, 717798, 717799,
724023, 724026, 724027, 724033,
724034, 724036, 724037, 724040,
724041, 724044, 724045, 724048,
724049, 724050, 724052, 724055,
724056, 724059, 724061, 724062,
724063, 724065, 724067, 724073,
724074, 724075, 724079, 724094,
724095, 724551, 724552, 724555,
724556, 724557, 724558, 724561,
724562, 724563, 724564, 724567,
724568, 724569, 724570, 724571,
724572, 724573, 724574, 724575,
724576, 724578, 724640, 724806,
724807, 724808, 724809, 724811,
724820, 724821, 724827, 724833,
724835, 724836, 724840, 724841,
724848, 724849, 724855, 724857,
724858, 724861, 724862, 724865,
724866, 724868, 724909, 724910,
724913, 724914, 724924, 724925,
724926, 724927, 727912, 728519,
728520, 728521, 728522, 728523,
728524, 728525, 728526, 728527,
728528, 728534, 728535, 728536,
728537, 728538, 728539, 728540,
728541, 728542, 728543, 728544,
728545, 728546, 728547, 728548,
728549, 728550, 728551, 728552,
728553, 728554, 728557, 728558,
728559, 728560, 728561, 728562,
728563, 728564
----------------------------------------------------------------------------------------------------------------
(3) PW4158. 717704, 724001, 724002, 724004, 4,300 5,600 6,600 750
724005, 724006, 724007, 724008,
724009, 724010, 724011, 724019,
724020, 724031, 724035, 724038,
724039, 724042, 724043, 724047,
724068, 724069, 724071, 724076,
724077, 724080, 724085, 724086,
724087, 724092, 724093, 724096,
724097, 724801, 724802, 724803,
724804, 724805, 724813, 724814,
724819, 724823, 724824, 724825,
724826, 724828, 724831, 724832,
724843, 724846, 724847, 724851,
724852, 724853, 724854, 724859,
724860, 724863, 724864, 724867,
724869, 724870, 724871, 724872,
724873, 724874, 724875, 724876,
724880, 724881, 724882, 724883,
724884, 724885, 724886, 724887,
724888, 724889, 724890, 724892,
724893, 724894, 724895, 724896,
724897, 724898, 724899, 724900,
724932, 727315, 727436, 728501,
728502, 728503, 728504, 728505,
728506, 728507, 728508, 728509,
728510, 728511, 728515, 728518,
728531, 728532, 728533
----------------------------------------------------------------------------------------------------------------
[[Page 38902]]
(4) PW4156, PW4156A, and All others not listed by SN in this 1,050 1,600 6,600 750
PW4158. Table.
----------------------------------------------------------------------------------------------------------------
(5) PW4052. All engines. 3,000 4,400 4,400 750
----------------------------------------------------------------------------------------------------------------
(6) PW4056. All engines. 1,800 3,000 3,000 750
----------------------------------------------------------------------------------------------------------------
(7) PW4060, PW4060A, PW4060C, All engines. 1,100 2,300 3,000 750
and PW4062.
----------------------------------------------------------------------------------------------------------------
Minimum Build Standard
(f) After the effective date of this AD, do not install an
engine with HPC and HPT modules where the CSO of the HPC is 1,500
cycles or more greater than the CSO of the HPT.
(g) After the effective date of this AD, any engine that
undergoes an HPC overhaul must meet the build standard of the
following PW SB's: PW4ENG 72-484, PW4ENG 72-486, PW4ENG 72-514, and
PW4ENG 72-575. Engines that incorporate the Phase 3 configuration
meet the build standard defined by PW SB PW4ENG 72-514.
(h) After the effective date of this AD, any engine that
undergoes separation of the HPC and HPT modules after the effective
date of this AD, must meet the build standard of PW SB PW4ENG 72-
514. Engines that incorporate the Phase 3 configuration meet the
build standard defined by PW SB PW4ENG 72-514.
(i) Within 100 CIS after the effective date of this AD, and
thereafter, limit the number of engines with configuration D from
Table 1 of this AD to one on each airplane.
(j) When a thrust rating change has been made by using the
Electronic Engine Control (EEC) programming plug in the affected HPC
overhaul period, the cyclic limits associated with the highest
thrust rating must be utilized.
Definitions
(k) For the purposes of this AD, the following definitions
apply:
(1) HPC Overhaul--an HPC overhaul is defined as restoration of
the HPC stages 5 through 15 blade tip clearances to the limits
specified in the applicable fits and clearances section of the
engine manual.
(2) HPT Overhaul--an HPT overhaul is defined as restoration of
the HPT module stage 1 and 2 HPT blade tip clearances to the
applicable fits and clearances section of the engine manual.
(3) A Phase 3 engine is identified by a (-3) suffix after the
engine model number on the data plate if incorporated at original
manufacture, or a (-3C) suffix after the engine model number if the
engine was converted using PW SB's PW4ENG 72-490, PW4ENG 72-504, or
PW4ENG 72-572 after original manufacture.
Alternative Methods of Compliance
(l) 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 (ECO).
Operators shall submit their requests through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, ECO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the ECO.
Special Flight Permits
(m) 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 airplane to a location where the
requirements of this AD can be accomplished.
Effective Date
(n) This amendment becomes effective August 10, 2001.
Issued in Burlington, Massachusetts on July 17, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 01-18432 Filed 7-25-01; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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