AD Amdt-39-9997
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Pratt & Whitney | PW2000 Series | Airworthiness Directives; Pratt & Whitney PW2000 Series Turbofan Engines |
Unsafe Condition
Cracks in the forward face of the first stage high pressure turbine (HPT) disks at the base of the fir tree lug at the outer diameter (OD) snap fillet radius where the side plates mate with the disk may lead to fir tree lug fracturing and uncontained disk failures.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect for cracks in the forward face of the first stage HPT disks at the specified location, rework the disks as required, and establish a new reduced cyclic life limit for certain disks.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pratt & Whitney PW2000 series turbofan engines
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney PW2000 series turbofan engines. This action requires initial and repetitive inspections for cracks in the forward face of the first stage high pressure turbine (HPT) disks at the base of the fir tree lug at the outer diameter (OD) snap fillet radius where the side plates mate with the disk, and rework to the first stage HPT disk. Additionally, this AD establishes a new, reduced cyclic life limit for certain disks. This amendment is prompted by reports of two uncontained disk failures resulting from a fir tree lug fracturing, subsequently releasing two blades and a fir tree lug, which penetrated the engine HPT turbine case. The actions specified in this AD are intended to prevent fracture of the first stage HPT disk, resulting in a possible uncontained engine failure and damage to the aircraft.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 62, Number 80 (Friday, April 25, 1997)]
[Rules and Regulations]
[Pages 20094-20098]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-10585]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-14; Amendment 39-9997; AD 97-09-01]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW2000 Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Pratt & Whitney PW2000 series turbofan engines. This
action requires initial and repetitive inspections for cracks in the
forward face of the first stage high pressure turbine (HPT) disks at
the base of the fir tree lug at the outer diameter (OD) snap fillet
radius where the side plates mate with the disk, and rework to the
first stage HPT disk. Additionally, this AD establishes a new, reduced
cyclic life limit for certain disks. This amendment
[[Page 20095]]
is prompted by reports of two uncontained disk failures resulting from
a fir tree lug fracturing, subsequently releasing two blades and a fir
tree lug, which penetrated the engine HPT turbine case. The actions
specified in this AD are intended to prevent fracture of the first
stage HPT disk, resulting in a possible uncontained engine failure and
damage to the aircraft.
DATES: Effective May 12, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 12, 1997.
Comments for inclusion in the Rules Docket must be received on or
before June 24, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-ANE-14, 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#680808513737090c37370d060f01060d181a0718280e0909460c071c460f071e">``<span class="__cf_email__" data-cfemail="9aa3c5c5fbfec5c5fff4fdf3f4ffeae8f5eadafcfbfbb4fef5eeb4fdf5ec">[email protected]</span></a>''. Comments sent via the Internet must
contain the docket number in the subject line.
The service information referenced in this AD 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 Assistant Chief Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: John Fisher, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7149, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA has received reports of two
fractured first stage high pressure turbine (HPT) disks on Pratt &
Whitney (PW) PW2000 series turbofan engines. The investigation revealed
higher than expected stresses in an area known as the forward face of
the first stage HPT disk at the base of the fir tree lug at the outer
diameter (OD) snap fillet radius where the side plates mate with the
disk. The FAA has determined that this snap fillet radius cannot be
adequately inspected utilizing the prior method of fluorescent
penetrant inspection, due to features on the disk that obstruct the
view of the snap fillet radius. Pratt & Whitney has subsequently
developed an eddy current inspection (ECI) probe which fits snugly into
the snap fillet radius area for significantly improved crack
detectability. In addition, the FAA has determined that the cracks form
prior to the currently published disk cyclic life limit. This
condition, if not corrected, could result in fracture of the first
stage HPT disk, resulting in a possible uncontained engine failure and
damage to the aircraft.
The FAA has reviewed and approved the technical contents of PW
Service Bulletin (SB) No. PW2000 72-588, Revision 1, dated March 31,
1997, that describes procedures for inspections for cracks in the
forward face of the first stage HPT disk at the base of the fir tree
lug at the OD snap fillet radius where the side plates mate with the
disk utilizing an eddy current inspection technique, and PW Alert
Service Bulletin (ASB) No. PW2000 A72-592, dated March 18, 1997, that
describes procedures for rework to the forward and aft faces of the
first stage HPT disk OD snap fillet radii at the base of the fir tree
lug.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design, this AD is
being issued to prevent a possible uncontained engine failure. The
disks were manufactured using different types of materials and
processing, and are identified by serial numbers. This AD requires
initial and repetitive ECI for cracks in the forward face of the first
stage HPT disk at the base of the fir tree lug at the OD snap fillet
radius where the side plates mate with the disk. The AD also requires
rework, consisting of removing material and increasing the radius of
both the forward and rear face of the disk at the base of the fir tree
lug where the side plates mate with the disk, and reidentification of
reworked parts. In addition, this AD establishes a new, reduced cyclic
life limit for disks that have been reworked prior to 5,000 cycles in
service since new (CSN). Accomplishing the rework lowers stresses and
assures that disks that are reworked after 5,000 CSN can reach the full
published cyclic life limit. Currently there is no terminating action
available to the inspection requirements of this AD. The actions are
required to be accomplished in accordance with the SB and ASB described
previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-ANE-14.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26,
[[Page 20096]]
1979). If it is determined that this emergency regulation otherwise
would be significant under DOT Regulatory Policies and Procedures, a
final regulatory evaluation will be prepared and placed in the Rules
Docket. A copy of it, if filed, may be obtained from the Rules Docket
at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [AMENDED]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
97-09-01 Pratt & Whitney: Amendment 39-9997. Docket 97-ANE-14.
Applicability: Pratt & Whitney (PW) PW2000 series turbofan
engines, installed on but not limited to Boeing 757 series, Ilyushin
IL-96 series, and McDonnell Douglas Model C-17 (military) aircraft.
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 (k) 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 fracture of the first stage high pressure turbine
(HPT) disk, resulting in a possible uncontained engine failure and
damage to the aircraft, accomplish the following:
(a) Prior to further flight, for first stage HPT disks that are
accessible in the shop, as defined in paragraph (j)(2) of this AD,
on the effective date of this AD, perform eddy current inspections
(ECI) of the first stage HPT disks for cracks in the forward face of
the disk at the base of the fir tree lug at the outer diameter (OD)
snap fillet radius where the side plates mate with the disk, in
accordance with the Accomplishment Instructions of PW Service
Bulletin (SB) No. PW2000 72-588, Revision 1, dated March 31, 1997,
or Original, dated February 17, 1997.
(b) For first stage HPT disks that are identified by serial
number (S/N) in Table 1 of this AD, rework the forward and aft faces
of the first stage HPT disk OD snap fillet radii at the base of the
fir tree lug in accordance with PW Alert Service Bulletin (ASB) No.
PW2000 A72-592, dated March 18, 1997, as follows:
Table 1
------------------------------------------------------------------------
------------------------------------------------------------------------
S/N
N54398 N54399 N54400 N54401
N54402 N54403 N54404 N54405
N54406 N54407 N54408 N54409
N54410 N54411 N54412 N54413
N54414 N54415 N54416 N54417
N54418 N54419 N55114 N55115
N55116 N55117 P00624 P00625
P00626 P00627 P00628 P00788
P00812 P00813 P00814 P00815
P00816 P00817 P00818 P00986
P00987 P01018 P01457 P36249
P36250 P36251 P36252 P36253
P36254 P36255 P36256 P36258
P36259 P36306 P36307 P36308
P36309 P36310 P36311 P36312
P36378 P36634 P36636 P36637
P36638 P36639 P36805 P36806
P37113 P37114 P37115 P37116
P37117 P37118 P37324 P37325
P37326 P37327 P37328 P37348
P37349 P37351 P37352 P37353
P37354 P90203 P90204 P90205
P90206 P90207 P90208 P90209
P90210 P90211 P90212 P90385
P90386 P90387 P90388 P90389
P90390 P91685 P91686 P91687
P91688 P91854 P91855 P91856
P91857 P91867 P91931 P91932
P91933 P91934 P91935 R28552
R28553 R28554 R28555 R28612
R28613 R28614 R28615 R28617
R28618 R28680 R28681 R28682
R28683 R28684 R28685 R28686
R28687 R28711 R28712 R28713
R28714 R28715 R28716 R28718
R28719 R28720 R28752 R28753
R28755 R28756 R28757 R28758
R28761 R28800 R28801 R28802
R28803 R28804 R28805 R28806
R28807 R28808 R28809 R28810
R28811 R28812 R28813 R28847
R28848 R28901 R28903 R28904
R28905 R28906 R28907 R28908
R28909 R28913 R28914 R28915
R28933 R28934 R28935 R28936
R28937 R28951 R28952 R28953
R28954 R28955 R28956 S16633
S16634 S16636 S16637 S16638
S16639 S16641 S16642 S16643
S16645 S16646 S16647 S16648
S16649 S16650 S16651 S16652
S16654 S16655 S16656 S16657
S16658 S16659 S16660 S16661
S16662 S16663 S16664 S16665
S16666 S16667 S16668 S16669
S16670 S16671 S16672 S16673
S16674 S16675 S16676 S16677
S16678 S16679 S16680 S16681
S16682 S16683 S16684 S16685
S16687 S16688 S16689 S16690
S16691 S16692 S16693 S16694
S16695 S16697 S16698 S16699
S16700 S16701 S16702 S16703
S16705 S16707 S16708 S16709
S16710 S16712 S16713 S16715
S16716 S16717 S16718 S16719
S16720 S16721 S16723 S16724
S16725 S16727 S16728 S16730
S16731 S16732 S16733 S16735
S16738 S16739 S16741 S16742
S16743 S16744 S16745 S16746
S16747 S16748 S16749 S16750
S16751 S16752 S16753 S16756
S16757 S16758 S16760 S16761
S16762 S16763 S16765 S16766
S16768 S16769 S16772 S16773
S16774 S16775 S16776 S16777
S16778 S16780 S16782 S16783
S16784 S16786 S16787 S16789
S16790 S16792 S16793 S16795
S16798 S16800 S16802 S16803
S16804 S16805 S16806 S16807
S16808 S16810 S16811 S16814
S16815 S16816 S16818 S16819
S16821 S16822 S16824 S16825
S16827 S16829 S16831 S16832
------------------------------------------------------------------------
(1) For disks that have accumulated 10,000 or more cycles since
new (CSN) on the effective date of this AD, inspect and rework
within 1,600 cycles in service (CIS) after the effective date of
this AD.
(2) For disks that have accumulated less than 10,000 CSN on the
effective date of this AD, inspect and rework at the next shop
visit, or 11,600 CSN, whichever occurs first.
(c) For first stage HPT disks that are identified by S/N in
Table 2 of this AD, rework the forward and aft faces of the first
stage HPT disk OD snap fillet radii at the base of the fir tree lug
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997,
as follows:
Table 2
------------------------------------------------------------------------
------------------------------------------------------------------------
S/N
M43410 M43411 M68250 M68251
M68252 M68253 M68254 M68255
M68256 M68344 M68345 M68346
M68347 M68348 M68349 M68350
M68536 M68537 M68538 M68539
M68540 M68541 M68696 M68697
M68698 M68699 M68700 M68701
M68702 M68703 M68915 M68916
M68917 M68918 M68919 M68997
M68998 M69000 M69001 M85382
M85383 M85384 M85385 M85386
M85387 N09764 N09765 N09766
N09767 N09768 N09769 N09770
N09771 N09772 N09773 N09774
N09775 N09776 N09777 N09778
N11389 N11390 N11391 N11392
N11393 N11394 N11395 N11396
N11397 N11398 N11399 N11400
N11401 N11402 N11403 N11404
N11405 N11406 N11407 N12830
N12831 N12832 N12833 N12834
N12835 N12836 N12838 N12839
N12840 N12841 N12842 N12843
[[Page 20097]]
N12844 N12845 N12846 N12847
N12848 N54390 N54391 N54392
N54393 N54395 N54396 N54397
------------------------------------------------------------------------
(1) For disks that have accumulated 7,000 or more CSN on the
effective date of this AD, inspect and rework within 800 CIS after
the effective date of this AD.
(2) For disks that have accumulated less than 7,000 CSN on the
effective date of this AD, inspect and rework at the next shop
visit, or 7,800 CSN, whichever occurs first.
(d) For first stage HPT disks that are identified by S/N in
Table 3 of this AD, rework the forward and aft faces of the first
stage HPT disk OD snap fillet radii at the base of the fir tree lug
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997,
as follows:
Table 3
------------------------------------------------------------------------
------------------------------------------------------------------------
D301AA0002 D301AA0003 D301AA0004
D301AA0005 D301AA0006 D301AA0008
D301AA0009 D301AA0010 D301AA0011
D301AA0013 D301AA0015 D301AA0018
D301AA0019 D301AA0020 D301AA0021
D301AA0022 D301AA0023 D301AA0024
D301AA0025 D301AA0027 D301AA0028
D301AA0029 D301AA0031 D301AA0032
D301AA0033 D301AA0034 D301AA0035
D301AA0038 D301AA0039 D301AA0040
D301AA0041 D301AA0042 D301AA0044
D301AA0045 D301AA0046 D301AA0047
D301AA0048 D301AA0049 D301AA0050
D301AA0051 D301AA0052 D301AA0053
D301AA0054 D301AA0055 D301AA0056
D301AA0057 D301AA0059 D301AA0061
D301AA0062 D301AA0064 D301AA0065
D301AA0066 D301AA0067 D301AA0068
D301AA0069 D301AA0070 D301AA0071
D301AA0072 D301AA0074 D301AA0075
D301AA0077 D301AA0080 D301AA0081
D301AA0082 D301AA0083 D301AA0084
D301AA0085 D301AA0086 D301AA0087
D301AA0088 D301AA0089 D301AA0090
D301AA0091 D301AA0092 D301AA0093
D301AA0094 D301AA0095 D301AA0096
D301AA0098 D301AA0101 D301AA0102
D301AA0103 D301AA0104 D301AA0105
D301AA0106 D301AA0107 D301AA0108
D301AA0110 D301AA0111 D301AA0114
D301AA0118 D301AA0121 D301AA0123
D301AA0124 D301AA0125 D301AA0127
D301AA0129 D301AA0130 D301AA0131
D301AA0132 D301AA0133 D301AA0135
D301AA0137 D301AA0138 D301AA0140
D301AA0141 D301AA0144 D301AA0145
D301AA0146 D301AA0147 D301AA0148
D301AA0149 D301AA0150 D301AA0151
D301AA0152 D301AA0154 D301AA0156
D301AA0157 D301AA0159 D301AA0161
D301AA0163 D301AA0164 D301AA0165
D301AA0166 D301AA0167 D301AA0171
D301AA0174 D301AA0175 D301AA0177
D301AA0179 D301AA0180 D301AA0182
D301AA0187 D301AA0189 D301AA0198
D301AA0201 D301AA0205 D301AA0358
D301AA0359 D301AA0360 D301AA0361
D301AA0362 D301AA0363 D301AA0364
D301AA0367 D301AA0368 D301AA0369
D301AA0370 D301AA0371 D301AA0372
D301AA0375 D301AA0376 D301AA0377
D301AA0379 D301AA0380 D301AA0381
D301AA0382 D301AA0383 D301AA0384
D301AA0386 D301AA0387 D301AA0388
D301AA0390 D301AA0391 D301AA0392
D301AA0393 D301AA0394 D301AA0395
D301AA0396 D301AA0399 D301AA0401
D301AA0402 D301AA0403 D301AA0404
D301AA0406 D301AA0407 D301AA0408
D301AA0412 D301AA0414 D301AA0415
D301AA0416 D301AA0418 D301AA0419
D301AA0420 D301AA0421 D301AA0422
D301AA0423 D301AA0424 D301AA0425
D301AA0426 D301AA0427 D301AA0428
D301AA0431 D301AA0432 D301AA0434
D301AA0435 D301AA0437 D301AA0438
D301AA0439 D301AA0440 D301AA0443
D301AA0444 D301AA0445 D301AA0446
D301AA0447 D301AA0449 D301AA0450
DKLBA78421 DKLBA78423 DKLBA78427
DKLBA78429 DKLBA78431 DKLBA78432
DKLBA78433 DKLBA78434 DKLBA78435
DKLBA78436 DKLBA78437 DKLBA78438
DKLBA78439 DKLBA78441 DKLBA78442
DKLBA78443 DKLBA78444 DKLBA78446
DKLBA78448 DKLBA78449 DKLBA78453
DKLBA78454 DKLBA78455 DKLBA78456
DKLBA78457 DKLBA78458 DKLBA78459
DKLBA78465 DKLBA78467 DKLBA78468
DKLBA78469 DKLBA78472 DKLBA78475
DKLBA78482 DKLBA78483 DKLBA78484
DKLBA78485 DKLBA78486 DKLBA78487
DKLBA78488 DKLBA78489 DKLBA78490
DKLBA78491 DKLBA78492 DKLBA78493
DKLBA78496 DKLBA78497 DKLBA78498
DKLBA78500 DKLBA78502 DKLBA78503
DKLBA78504 DKLBA78505 DKLBA78506
DKLBA78507 DKLBA78508 DKLBA78509
DKLBA78510 DKLBA78512 DKLBA78514
DKLBA78515 DKLBA78517 DKLBA78518
DKLBA78519 DKLBA78520 DKLBA78521
DKLBA78522 DKLBA78524 DKLBA78525
DKLBA78526 DKLBA78527 DKLBA78528
DKLBA78529 DKLBA78530 DKLBA78531
DKLBA78533 DKLBA78534 DKLBA78536
DKLBA78537 DKLBA78538 DKLBA78540
DKLBA78541 DKLBA78542 DKLBA78543
DKLBA78544 DKLBA78545 DKLBA78550
DKLBA78551 DKLBA78552 DKLBA78553
DKLBA78554 DKLBA78557 DKLBA78558
DKLBA78559 DKLBA78560 DKLBA78561
DKLBA78562 DKLBA78564 DKLBA78568
DKLBA78569 DKLBA78575 DKLBA78577
DKLBA78578 DKLBA78579 DKLBA78580
DKLBA78581 DKLBA78582 DKLBA78584
DKLBA78585 DKLBA78587 DKLBA78589
DKLBA78590 DKLBA78593 DKLBA78594
DKLBA78596 DKLBA78598 DKLBA78600
DKLBA78601 DKLBA78603 DKLBA78604
DKLBA78605 DKLBA78606 DKLBA78607
DKLBA78609 DKLBA78610 DKLBA78611
DKLBA78613 DKLBA78614 DKLBA78615
DKLBA78616 DKLBA78617 DKLBA78618
DKLBA78620 DKLBA78622 DKLBA78625
DKLBA78627 DKLBA78628 DKLBA78632
DKLBA78633 DKLBA78635 DKLBA78636
DKLBA78638 DKLBA78639 DKLBA78640
DKLBA78642 DKLBA78644 DKLBA78645
DKLBA78646 DKLBA78648 DKLBA78649
DKLBA78650 DKLBA78651 DKLBA78652
DKLBA78653 DKLBA78654 DKLBA78655
DKLBA78656 DKLBA78657 DKLBA78658
DKLBA78660 DKLBA78661 DKLBAH8318
DKLBAH8319 DKLBAH8320 DKLBAH8321
DKLBAH8322 DKLBAH8323 DKLBAH8324
DKLBAH8325 DKLBAH8327 DKLBAH8328
DKLBAH8329 DKLBAH8330 DKLBAH8331
DKLBAH8332 DKLBAH8333 DKLBAH8336
DKLBAH8337 DKLBAH8339 DKLBAH8340
DKLBAH8343 DKLBAH8344 DKLBAH8346
DKLBAH8347 DKLBAH8348 DKLBAH8349
DKLBAH8350 DKLBAH8351 DKLBAH8352
DKLBAH8353 DKLBAH8354 DKLBAH8355
DKLBAH8356 DKLBAH8357 DKLBAH8360
DKLBAH8361 DKLBAH8362 DKLBAH8364
DKLBAH8365 DKLBAM0972 DKLBAM0973
L82270 L82271 L82272
L82356 L82649 L82650
L83308 L83309 L83310
L83311 L83312 M15709
M15710 M15718 M42710
M42711 M42768 M42769
M42770 M42771 M43103
M43104 M43105 M43396
M43397 M43398 M43399
M43400 M43401 M43409
------------------------------------------------------------------------
(1) For disks that have accumulated 7,000 or more CSN on the
effective date of this AD, inspect and rework within 1,100 CIS after
the effective date of this AD.
(2) For disks that have accumulated less than 7,000 CSN on the
effective date of this AD, inspect and rework at the next shop
visit, or 8,100 CSN, whichever occurs first.
(e) For disks that have previously been inspected in accordance
with PW SB No. PW2000 72-588, Revision 1, dated March 31, 1997, or
Original, dated February 17, 1997, but not reworked in accordance
with PW ASB No. PW2000 A72-592, dated March 18, 1997, rework in
accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997, at
the next shop visit when the part is accessible, as defined in
paragraph (j)(2) of this AD, or 4,000 CIS since inspection in
accordance with PW SB No. PW2000 72-588, Revision 1, dated March 31,
1997, or Original, dated February 17, 1997, whichever occurs first.
(f) Prior to further flight, remove and replace disks with
cracks. Disks with cracks cannot be reworked.
(g) If reworked, reidentify the disk in accordance with the
Accomplishment Instructions of PW ASB No. PW2000 A72-592, dated
March 18, 1997.
(h) For all first stage HPT disks that have been reworked in
accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997,
thereafter inspect in accordance with PW Temporary Revision 72-937,
dated April 11, 1997, to Engine Manual, P/N 1A6231, Section 72-52-
02, Inspection Check 04, at each subsequent shop visit when the disk
is accessible, as defined in paragraph (j)(2) of this AD, not to
exceed 6,000 CIS since last inspection.
(i) The following cyclic life limits apply to disks that are
reworked in accordance with the Accomplishment Instructions of PW
Alert Service Bulletin (ASB) No. PW2000 A72-592, dated March 18,
1997:
(1) Disks that have accumulated less than 5,000 CSN upon rework
may accumulate an additional 10,000 CIS following rework, and then
must be retired from service.
(2) Disks that have accumulated 5,000 CSN or more upon rework
may remain in service to the full 15,000 CSN published life limit,
and then must be retired from service.
(3) Except as provided in paragraph (k) of this AD, no
alternative life limits may be approved for disks reworked in
accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(j) For the purpose of this AD, the following definitions apply:
(1) A shop visit is defined as an engine removal where engine
maintenance, prior to reinstalling the engine, entails separation of
pairs of mating major engine flanges or the removal of a disk, hub,
or spool.
(2) An accessible disk is defined as a disk that is in the shop,
has been removed from the HPT module, separated from the rotor, and
debladed.
[[Page 20098]]
(k) 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 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(l) 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 inspection and rework requirements of this AD can be
accomplished.
(m) The actions required by this AD shall be done in accordance
with the following PW service documents:
----------------------------------------------------------------------------------------------------------------
Document No. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
SB No. PW2000
72-588......................... 1 1................................ Mar. 31, 1997.
2 Original......................... Feb. 17, 1997.
3-12 1................................ Mar. 31, 1997.
NDIP-899........................... 1-23 A................................ Mar. 25, 1997.
Total Pages: 35
SB No. PW2000
72-588......................... 1-12 Original......................... Feb. 17, 1997.
NDIP-899........................... 1-23 Original......................... Feb. 16, 1997.
SB No. PW2000
72-588......................... 38 Original......................... Feb. 17, 1997.
Total Pages: 36
ASB No. PW2000
A72-592........................ 1-16 Original......................... Mar. 18, 1997.
Total Pages: 16
----------------------------------------------------------------------------------------------------------------
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 St., East
Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503.
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.
(n) This amendment becomes effective on May 12, 1997.
Issued in Burlington, Massachusetts, on April 17, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-10585 Filed 4-24-97; 8:45 am]
BILLING CODE 4910-13-U
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
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