[Federal Register Volume 62, Number 152 (Thursday, August 7, 1997)]
[Rules and Regulations]
[Pages 42391-42397]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-20784]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-25-AD; Amendment 39-10094, AD 97-11-51 R1]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW2000 Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Pratt & Whitney PW2000 series turbofan engines. This
action revises telegraphic AD T97-11-51 that currently supersedes AD
97-09-01 by correcting errors in the Serial Number (S/N) tables, and
removing the McDonnell Douglas C-17 aircraft from the applicability
section, as a different model engine is installed on McDonnell Douglas
C-17 aircraft. In addition, that telegraphic AD clarifies that
inspections must be performed prior to rework, and clarifies that new
parts do not need to be reworked prior to installation, but must be
reworked at the next shop visit. Finally, that telegraphic AD makes
minor editorial changes for clarity without changing meaning or intent.
This action relaxes the compliance intervals for rework and provides
relieving requirements. This amendment is prompted by industry input
and resulting changes by the manufacturer to the inspection program
that would provide relief to operators while maintaining an equivalent
level of safety. The actions specified by this AD are intended to
prevent fracture of the first stage high pressure turbine (HPT) disk,
resulting in a possible uncontained engine failure and damage to the
aircraft.
DATES: August 7, 1997.
[[Page 42392]]
The incorporation by reference of certain publications listed in
the regulations was approved by the Director of the Federal Register as
of May 10, 1997.
Comments for inclusion in the Rules Docket must be received on or
before October 6, 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-25-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. 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 Certificate 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: On May 12, 1997, the Federal Aviation
Administration (FAA) issued telegraphic airworthiness directive (AD)
T97-11-51, applicable to Pratt & Whitney (PW) PW2000 series turbofan
engines, which supersedes AD 97-09-01 by correcting errors in the
Serial Number (S/N) tables, and removing the McDonnell Douglas C-17
aircraft from the applicability section, as a different model engine is
installed on McDonnell Douglas C-17 aircraft. In addition, that AD
clarifies that inspections must be informed prior to rework, and
clarifies that new parts do not need to be reworked prior to
installation, but must be reworked at the next shop visit. Finally,
that AD makes minor editorial changes for clarity without changing
meaning or intent. That action was prompted by comments from the
manufacturer received in response to AD 97-09-01 that require the FAA
to issue immediate changes and corrections to the compliance section
prior to initiating the inspection and rework program described in the
AD 97-09-01. Airworthiness directive 97-09-01 was prompted by reports
of two uncontained disk failures resulting from a fir tree lug
fracturing, that subsequently released two blades and a fir tree lug,
that penetrated the engine high pressure turbine (HPT) case. That
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.
Since the issuance of that telegraphic AD, the FAA has received
changes from the manufacturer to the inspection program that would
provide relief to operators while maintaining an equivalent level of
safety.
The FAA has reviewed and approved the technical contents of PW
Service Bulletin (SB) No. PW2000 72-588, Revision 1, dated March 31,
1997, and Original, dated February 17, 1997, that describe 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 outer diameter (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 this same type design, this AD
revises telegraphic AD T97-11-51 to relax the compliance intervals for
rework and provide relieving requirements by adding an optional double
independent eddy current inspection. The actions are required to be
accomplished in accordance with the service documents 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-25-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 42393]]
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:
97-11-51 R1 Pratt & Whitney: Amendment 39-10094. Docket No. 97-ANE-
25-AD. Revises AD T97-11-51.
Applicability: Pratt & Whitney (PW) PW2000 series turbofan
engines, with first stage high press turbine (HPT) disk assembly,
Part Numbers (P/N) 1A5921, 1B2671, and 1B3621, installed. These
engines are installed on but not limited to Boeing 757 series and
Ilyushin IL-96 series 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 (1) 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 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, on the effective date of this AD, as defined
in paragraph (k)(2) of this AD, and that have not been eddy current
inspected 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, perform eddy current
inspection (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 plants mate
with the disk, in accordance with the Accomplishment Instructions of
PW 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, and have not been eddy current
inspected in accordance with the Accomplishment Instructions of PW
SB No. PW2000 72-588, Revision 1, dated March 31, 1997, or Original,
dated February 17, 1997, accomplish the following:
Table 1
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L82270......... M68538 N11397 N54412 P36638 P91935 R28848
L82271......... M68539 N11398 N54413 P36639 R28552 R28901
L82272......... M68540 N11399 N54414 P36805 R28553 R28903
L82356......... M68541 N11400 N54415 P36806 R28554 R28904
L82649......... M68696 N11401 N54416 P37113 R28555 R28905
L82650......... M68697 N11402 N54417 P37114 R28612 R28906
L83308......... M68698 N11403 N54418 P37115 R28613 R28907
L83309......... M68699 N11404 N54419 P37116 R28614 R28908
L83310......... M68700 N11405 N55114 P37117 R28615 R28909
L83311......... M68701 N11406 N55115 P37118 R28617 R28913
L83312......... M68702 N11407 N55116 P37324 R28618 R28914
M15709......... M68703 N12830 N55117 P37325 R28680 R28915
M15710......... M68915 N12831 P00624 P37326 R28681 R28933
M15718......... M68916 N12832 P00625 P37327 R28682 R28934
M42710......... M68917 N12833 P00626 P37328 R28683 R28935
M42711......... M68918 N12834 P00627 P37348 R28684 R28936
M42768......... M68919 N12835 P00628 P37349 R28685 R28937
M42769......... M68997 N12836 P00788 P37351 R28686 R28951
M42770......... M68998 N12838 P00812 P37352 R28687 R28952
M42771......... M69000 N12839 P00813 P37353 R28711 R28953
M43103......... M69001 N12840 P00814 P37354 R28712 R28954
M43104......... M85382 N12841 P00815 P90203 R28713 R28955
M43105......... M85383 N12842 P00816 P90204 R28714 R28956
M43396......... M85384 N12843 P00817 P90205 R28715 S16633
M43397......... M85385 N12844 P00818 P90206 R28716 S16634
M43398......... M85386 N12845 P00986 P90207 R28718 S16636
M43399......... M85387 N12846 P00987 P90208 R28719 S16637
M43400......... N09764 N12847 P01018 P90209 R28720 S16638
M43401......... N09765 N12848 P01457 P90210 R28752 S16639
M43409......... N09766 N54390 P36249 P90211 R28753 S16641
M43410......... N09767 N54391 P36250 P90212 R28755 S16642
M43411......... N09768 N54392 P36251 P90385 R28756 S16643
M68250......... N09769 N54393 P36252 P90386 R28757 S16645
M68251......... N09770 N54395 P36253 P90387 R28758 S16646
M68252......... N09771 N54396 P36254 P90388 R28761 S16647
M68253......... N09772 N54397 P36255 P90389 R28800 S16648
M68254......... N09773 N54398 P36256 P90390 R28801 S16649
M68255......... N09774 N54399 P36258 P91685 R28802 S16650
M68256......... N09775 N54400 P36259 P91686 R28803 S16651
M68344......... N09776 N54401 P36306 P91687 R28804 S16658
M68345......... N09777 N54402 P36307 P91688 R28805 S16659
M68346......... N09778 N54403 P36308 P91854 R28806 S16660
M68347......... N11389 N54404 P36309 P91855 R28807 S16662
M68348......... N11390 N54405 P36310 P91856 R28808 S16666
M68349......... N11391 N54406 P36311 P91857 R28809 S16678
M68350......... N11392 N54407 P36312 P91867 R28810 S16687
[[Page 42394]]
M68536......... N11393 N54408 P36378 P91931 R28811
M68537......... N11394 N54409 P36634 P91932 R28812
N11395 N54410 P36636 P91933 R28813
N11396 N54411 P36637 P91934 R28847
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(1) For disks that have accumulated 10,000 or more cycles since
new (CSN) on the effective date of this AD, accomplish the
following:
(i) Perform an inspection for cracks and rework within 1,600 CIS
after the effective date of this AD in accordance with PW ASB No.
PW2000 A72-592, dated March 18, 1997, or
Note 2: Throughout this AD, Pratt & Whitney ASB No. PW2000 A72-
592, dated March 18, 1997, describes returning the part to
designated overhaul shops for modifications. The modifications
described in that ASB are performed by the overhaul shops and
include inspections prior to and after rework.
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, within 1,600 cycles in
service (CIS) after the effective date of this AD, in accordance
with the Accomplishment Instructions of PW SB No. PW2000 72-588,
Revision 1, dated March 31, 1997, or Original, dated February 17,
1997.
(iii) If the disk is double inspected in accordance with
paragraph (b)(1)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 4,000 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(2) For disks that have accumulated less than 10,000 CSN on the
effective date of this AD, accomplish the following:
(i) Perform an inspection for cracks and rework at the next shop
visit after the effective date of this AD, or 11,600 CSN, whichever
occurs first, in accordance with PW ASB No. PW2000 A72-592, dated
March 18, 1997, or
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, at the next shop visit after
the effective date of this AD, not to exceed 11,600 CSN, in
accordance with the Accomplishment Instructions of PW SB No. PW2000
72-588, Revision 1, dated March 31, 1997, or Original, dated
February 17, 1997.
(iii) If the disk is double inspected in accordance with
paragraph (b)(2)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 4,000 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(c) For first stage HPT disks that are identified by S/N in
Table 2 of this AD, and that have not been eddy current inspected in
accordance with the Accomplishment Instructions of PW SB No. PW2000
72-588, Revision 1, dated March 31, 1997, or Original, dated
February 17, 1997, accomplish the following:
Table 2
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D301AA0011........... S16682 S16713 S16746 S16780
D301AA0032........... S16683 S16715 S16747 S16783
S16652............... S16684 S16716 S16748 S16787
S16654............... S16685 S16717 S16749 S16795
S16655............... S16688 S16718 S16750
S16656............... S16689 S16719 S16751
S16657............... S16690 S16720 S16752
S16661............... S16691 S16721 S16753
S16663............... S16692 S16723 S16756
S16664............... S16693 S16724 S16757
S16665............... S16694 S16725 S16758
S16667............... S16695 S16727 S16760
S16668............... S16697 S16728 S16761
S16669............... S16698 S16730 S16762
S16670............... S16699 S16731 S16763
S16671............... S16700 S16732 S16765
S16672............... S16701 S16733 S16766
S16673............... S16702 S16735 S16768
S16674............... S16703 S16738 S16769
S16675............... S16705 S16739 S16772
S16676............... S16707 S16741 S16773
S16677............... S16708 S16742 S16774
S16679............... S16709 S16743 S16775
S16680............... S16710 S16744 S16776
S16681............... S16712 S16745 S16777
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(1) For disks that have accumulated 7,000 or more CSN on the
effective date of this AD, accomplish the following:
(i) Perform an inspection for cracks and rework within 800 CIS
after the effective date of this AD in accordance with PS ASB No.
PW2000 A72-592, dated March 18, 1997, or
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, within 800 CIS after the
effective date of this AD, in accordance with the Accomplishment
Instructions of PW SB No. PW2000 72-588, Revision 1, dated March 31,
1997, or Original, dated February 17, 1997.
(iii) If the disk is double inspected in accordance with
paragraph (c)(1)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 4,000 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(2) For disks that have accumulated less then 7,000 CSN on the
effective date of this AD, accomplish the following:
(i) Perform an inspection for cracks and rework at the next shop
visit after the effective date of this AD, or 7,800 CSN, whichever
occurs first, in accordance with PW ASB No. PW2000 A72-592, dated
March 18, 1997, or
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, at the next shop visit after
the effective date of this AD, not to exceed 7,800 CSN, in
accordance with the Accomplishment Instructions of PW SB No. PW2000
72-588, Revision 1, dated March 31, 1997, or Original, dated
February 17, 1997.
[[Page 42395]]
(iii) If the disk is double inspected in accordance with
paragraph (c)(2)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 4,000 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(d) For first stage HPT disks that are identified by S/N in
Table 3 of this AD, and that have not been eddy current inspected in
accordance with the Accomplishment Instructions of PW SB No. PW2000
72-588, Revision 1, dated March 31, 1997, or Original, dated
February 17, 1997, accomplish the following:
Table 3
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----------------------------------------------------------------------------------------------------------------
D301AA0002....... D301AA0094 D301AA0371 DKLBA78442 DKLBA78551 DKLBA78661
D301AA0003....... D301AA0095 D301AA0372 DKLBA78443 DKLBA78552 DKLBAH8318
D301AA0004....... D301AA0096 D301AA0375 DKLBA78444 DKLBA78553 DKLBAH8319
D301AA0005....... D301AA0098 D301AA0376 DKLBA78446 DKLBA78554 DKLBAH8320
D301AA0006....... D301AA0101 D301AA0377 DKLBA78448 DKLBA78557 DKLBAH8321
D301AA0008....... D301AA0102 D301AA0379 DKLBA78449 DKLBA78558 DKLBAH8322
D301AA0009....... D301AA0103 D301AA0380 DKLBA78453 DKLBA78559 DKLBAH8323
D301AA0010....... D301AA0104 D301AA0381 DKLBA78454 DKLBA78560 DKLBAH8324
D301AA0013....... D301AA0105 D301AA0382 DKLBA78455 DKLBA78561 DKLBAH8325
D301AA0015....... D301AA0106 D301AA0383 DKLBA78456 DKLBA78562 DKLBAH8327
D301AA0018....... D301AA0107 D301AA0384 DKLBA78457 DKLBA78564 DKLBAH8328
D301AA0019....... D301AA0108 D301AA0386 DKLBA78458 DKLBA78568 DKLBAH8329
D301AA0020....... D301AA0110 D301AA0387 DKLBA78459 DKLBA78569 DKLBAH8330
D301AA0021....... D301AA0111 D301AA0388 DKLBA78465 DKLBA78575 DKLBAH8331
D301AA0022....... D301AA0114 D301AA0390 DKLBA78467 DKLBA78577 DKLBAH8332
D301AA0023....... D301AA0118 D301AA0391 DKLBA78468 DKLBA78578 DKLBAH8333
D301AA0024....... D301AA0121 D301AA0392 DKLBA78469 DKLBA78579 DKLBAH8336
D301AA0025....... D301AA0123 E301AA0393 DKLBA78472 DKLBA78580 DKLBAH8337
D301AA0027....... D301AA0124 E301AA0394 DKLBA78475 DKLBA78581 DKLBAH8339
D301AA0028....... D301AA0125 D301AA0395 DKLBA78482 DKLBA78582 DKLBAH8340
D301AA0029....... D301AA0127 D301AA0396 DKLBA78483 DKLBA78584 DKLBAH8343
D301AA0031....... D301AA0129 D301AA0399 DKLBA78484 DKLBA78585 DKLBAH8344
D301AA0033....... D301AA0130 D301AA0401 DKLBA78485 DKLBA78587 DKLBAH8346
D301AA0034....... D301AA0131 D301AA0402 DKLBA78486 DKLBA78589 DKLBAH8347
D301AA0035....... D301AA0132 D301AA0403 DKLBA78487 DKLBA78590 DKLBAH8348
D301AA0038....... D301AA0133 D301AA0404 DKLBA78488 DKLBA78593 DKLBAH8349
D301AA0039....... D301AA0135 D301AA0406 DKLBA78489 DKLBA78594 DKLBAH8350
D301AA0040....... D301AA0137 D301AA0407 DKLBA78490 DKLBA78596 DKLBAH8351
D301AA0041....... D301AA0138 D301AA0408 DKLBA78491 DKLBA78598 DKLBAH8352
D301AA0042....... D301AA0140 D301AA0412 DKLBA78492 DKLBA78600 DKLBAH8353
D301AA0044....... D301AA0141 D301AA0414 DKLBA78493 DKLBA78601 DKLBAH8354
D301AA0045....... D301AA0144 D301AA0415 DKLBA78496 DKLBA78603 DKLBAH8355
D301AA0046....... D301AA0145 D301AA0416 DKLBA78497 DKLBA78604 DKLBAH8356
D301AA0047....... D301AA0146 D301AA0418 DKLBA78498 DKLBA78605 DKLBAH8357
D301AA0048....... D301AA0147 D301AA0419 DKLBA78500 DKLBA78606 DKLBAH8360
D301AA0049....... D301AA0148 D301AA0420 DKLBA78502 DKLBA78607 DKLBAH8361
D301AA0050....... D301AA0149 D301AA0421 DKLBA78503 DKLBA78609 DKLBAH8362
D301AA0051....... D301AA0150 D301AA0422 DKLBA78504 DKLBA78610 DKLBAH8364
D301AA0052....... D301AA0151 D301AA0423 DKLBA78505 DKLBA78611 DKLBAH8365
D301AA0053....... D301AA0152 D301AA0424 DKLBA78506 DKLBA78613 DKLBAM0972
D301AA0054....... D301AA0154 D301AA0425 DKLBA78507 DKLBA78614 DKLBAM0973
D301AA0055....... D301AA0156 D301AA0426 DKLBA78508 DKLBA78615 S16778
D301AA0056....... D301AA0157 D301AA0427 DKLBA78509 DKLBA78616 S16782
D301AA0057....... D301AA0159 D301AA0428 DKLBA78510 DKLBA78617 S16784
D301AA0059....... D301AA0161 D301AA0431 DKLBA78512 DKLBA78618 S16786
D301AA0061....... D301AA0163 D301AA0432 DKLBA78514 DKLBA78620 S16789
D301AA0062....... D301AA0164 D301AA0434 DKLBA78515 DKLBA78622 S16790
D301AA0064....... D301AA0165 D301AA0435 DKLBA78517 DKLBA78625 S16792
D301AA0065....... D301AA0166 D301AA0437 DKLBA78518 DKLBA78627 S16793
D301AA0066....... D301AA0167 D301AA0438 DKLBA78519 DKLBA78628 S16798
D301AA0067....... D301AA0171 D301AA0439 DKLBA78520 DKLBA78632 S16800
D301AA0068....... D301AA0174 D301AA0440 DKLBA78521 DKLBA78633 S16802
D301AA0069....... D301AA0175 D301AA0443 DKLBA78522 DKLBA78635 S16803
D301AA0070....... D301AA0177 D301AA0444 DKLBA78524 DKLBA78636 S16804
D301AA0071....... D301AA0179 D301AA0445 DKLBA78525 DKLBA78638 S16805
D301AA0072....... D301AA0180 D301AA0446 DKLBA78526 DKLBA78639 S16806
D301AA0074....... D301AA0182 D301AA0447 DKLBA78527 DKLBA78640 S16807
D301AA0075....... D301AA0187 D301AA0449 DKLBA78528 DKLBA78642 S16808
D301AA0077....... D301AA0189 D301AA0450 DKLBA78529 DKLBA78644 S16810
D301AA0080....... D301AA0198 DKLBA78421 DKLBA78530 DKLBA78645 S16811
D301AA0081....... D301AA0201 DKLBA78423 DKLBA78531 DKLBA78646 S16814
D301AA0082....... D301AA0205 DKLBA78427 DKLBA78533 DKLBA78648 S16815
D301AA0083....... D301AA0358 DKLBA78429 DKLBA78534 DKLBA78649 S16816
D301AA0084....... D301AA0359 DKLBA78431 DKLBA78536 DKLBA78650 S16818
D301AA0085....... D301AA0360 DKLBA78432 DKLBA78537 DKLBA78651 S16819
D301AA0086....... D301AA0361 DKLBA78433 DKLBA78538 DKLBA78652 S16821
D301AA0087....... D301AA0362 DKLBA78434 DKLBA78540 DKLBA78653 S16822
[[Page 42396]]
D301AA0088....... D301AA0363 DKLBA78435 DKLBA78541 DKLBA78654 S16824
D301AA0089....... D301AA0364 DKLBA78436 DKLBA78542 DKLBA78655 S16825
D301AA0090....... D301AA0367 DKLBA78437 DKLBA78543 DKLBA78656 S16827
D301AA0091....... D301AA0368 DKLBA78438 DKLBA78544 DKLBA78657 S16829
D301AA0092....... D301AA0369 DKLBA78439 DKLBA78545 DKLBA78658 S16831
D301AA0093....... D301AA0370 DKLBA78441 DKLBA78550 DKLBA78660 S16832
----------------------------------------------------------------------------------------------------------------
(1) For disks that have accumulated 7,000 or more CSN on the
effective date of this AD accomplish the following:
(i) Perform an inspection for cracks and rework within 1,100 CIS
after the effective date of this AD in accordance with PW ASB No.
PW2000 A72-592, dated March 18, 1997, or
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, within 1,100 CIS after the
effective date of this AD, in accordance with the Accomplishment
Instructions of PW SB No. PW2000 72-588, Revision 1, dated March 31,
1997, or Original, dated February 17, 1997.
(iii) If the disk is double inspected in accordance with
paragraph (d)(1)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 2,450 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(2) For disks that have accumulated less than 7,000 CSN on the
effective date of this AD, accomplish the following:
(i) Perform an inspection for cracks and rework at the next shop
visit after the effective date of this AD, or 8,100 CSN, whichever
occurs first, in accordance with PW ASB No. PW2000 A72-592, dated
March 18, 1997, or
(ii) Perform a double independent inspection for cracks, as
defined in paragraph (k)(3) of this AD, at the next shop visit after
the effective date of this AD, not to exceed 8,100 CSN, in
accordance with the Accomplishment Instructions of PW SB No. PW2000
72-588, Revision 1, dated March 31, 1997, or Original, dated
February 17, 1997.
(iii) If the disk is double inspected in accordance with
paragraph (d)(2)(ii) of this AD, then inspect the disk for cracks
and rework at the next shop visit after the completion of the double
inspection, but not to exceed 2,450 CIS since the double inspection,
in accordance with PW ASB No. PW2000 A72-592, dated March 18, 1997.
(e) For disks that have 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, inspect for cracks and
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 (k)(2) of this AD, or 4,000 CIS since last ECI 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,
inspect in accordance with PW 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 (k)(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
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 (1) 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) Operators may install new, unused first stage HPT disks
without inspection and rework in accordance with PW ASB No. PW2000
A72-592, dated March 18, 1997, but must inspect and rework those
disks at the next shop visit when the disk is accessible, as defined
in paragraph (k)(2) of this AD, or 6,500 CSN, whichever occurs
first, in accordance with PW ASB No. PW2000 A72-592, dated March 18,
1997, as defined in paragraphs (b) through (d), and (f) through (i)
of this AD.
(k) 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.
(3) A double independent inspection is defined as having two
independent qualified inspectors perform a complete ECI of the disk
in accordance with the inspection requirements described in the
Accomplishment Instructions of PW SB No. PW2000 72-588, Revision 1,
dated March 31, 1997, or Original, dated February 17, 1997. Each
inspector shall perform an independent calibration of the ECI
equipment prior to performing the ECI in accordance with that SB.
(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.
Operators shall submit their requests 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.
(m) 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.
(n) The actions required by this AD shall be accomplished in
accordance with the following PW service documents:
----------------------------------------------------------------------------------------------------------------
Document No. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
SB No. PW2000
72-588............................... 1.................... 1........................ March 31, 1997.
2.................... Original................. February 17, 1997.
3-12................. 1........................ March 31, 1997.
NDIP-899............................. 1-23................. A........................ March 25, 1997.
38................... Original................. February 17, 1997.
Total pages: 36
SB No. PW2000
[[Page 42397]]
72-588............................... 1-12................. Original................. February 17, 1997.
38................... Original................. February 17, 1997.
NDIP-899............................. 1-23................. Original................. February 16, 1997.
Total pages: 36
ASB No. PW2000
A72-592.............................. 1-16................. Original................. March 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.
(o) This amendment becomes effective on August 7, 1997.
Issued in Burlington, Massachusetts, on July 25, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-20784 Filed 8-6-97; 8:45 am]
BILLING CODE 4910-13-M
