[Federal Register Volume 63, Number 37 (Wednesday, February 25, 1998)]
[Rules and Regulations]
[Pages 9405-9408]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4408]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-04-AD; Amendment 39-10351; AD 98-04-39]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D 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 (PW) JT8D series turbofan engines.
This action requires a one-time borescope inspection of the combustion
chamber outer case (CCOC) for cracks on engines identified by serial
number that were ultrasonically inspected in accordance with AD 96-23-
14 with defective probes. In addition, this AD requires an ultrasonic
probe functional check at PW prior to using the probe to perform an
ultrasonic inspection if the probe was overhauled, repaired, or
otherwise altered since original manufacture and not subsequently
functionally checked by PW. This amendment is prompted by reports of
defective probes discovered in the field. The actions specified in this
AD are intended to prevent uncontained engine failure, inflight engine
shutdown, engine cowl release, and airframe damage.
DATES: Effective February 25, 1998.
The incorporation by reference of Pratt & Whitney Alert Service
Bulletin No. A6202, Revision 1, dated January 4, 1996, as listed in the
regulations, was approved previously by the Director of the Federal
Register as of January 2, 1997 (61 FR 63707, December 2, 1996).
Comments for inclusion in the Rules Docket must be received on or
before April 27, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-04-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 Regional 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: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On November 7, 1996, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 96-23-14,
Amendment 39-9820 (61 FR 63707, December 2, 1996), which supersedes ADs
87-11-07 R1 and 95-08-15, to require repetitive eddy current,
fluorescent penetrant, fluorescent magnetic particle, or visual
inspections for cracks in the rear flange, and ultrasonic, fluorescent
penetrant, or fluorescent magnetic particle inspections for cracks in
the PS4 boss, and drain bosses of the combustion chamber outer case
(CCOC); and an additional inspection of the CCOC rear flange for
intergranular cracking. In addition, AD 96-23-14 reduces the rear
flange inspection interval for CCOCs when only the aft face of the rear
flange has been inspected, and introduces an improved ultrasonic probe
assembly. Also, AD 96-23-14 introduces a rotating eddy current probe
for shop inspections in which the case is removed from the engine.
Finally, AD 96-23-14 eliminates fluorescent penetrant inspection (FPI),
fluorescent magnetic particle inspection (FMPI), and visual inspections
from hot section disassembly level inspection procedures. That action
was prompted by reports of crack origins in the forward face of the
rear flange that could not be detected by the inspection methods for
installed CCOCs that were mandated in the superseded ADs 87-11-07 R1
and 95-08-15. That condition, if not corrected, could result in
uncontained engine failure, inflight engine shutdown, engine cowl
release, and airframe damage.
Since the issuance of AD 96-23-14, the FAA has received reports of
13
[[Page 9406]]
defective ultrasonic inspection probes used to accomplish the
ultrasonic inspections required by AD 96-23-14. Those 13 defective
probes have been identified and removed from the field, but the engines
inspected with the defective probes must be reinspected. Other
ultrasonic inspection probes were either overhauled, repaired, or
otherwise altered since original manufacture and were not subsequently
functionally checked to insure that they met the necessary inspection
sensitivity requirements. The calibration check contained in the
ultrasonic inspection procedure does not serve as an adequate check to
insure that the probe meets inspection sensitivity requirements.
Currently, only PW has the capability to perform the necessary
functional check to the proper standard.
The FAA has reviewed and approved the technical contents of PW
Alert Service Bulletin (ASB) No. A6202, Revision 1, dated January 4,
1996, that describes procedures for a borescope inspection of the CCOC
rear flange for cracks. This ASB identifies applicability to engines
installed on McDonnell Douglas DC-9 and Boeing 737 series engines only;
however, the inspection requirements of paragraph 2.A.(5) of PW ASB No.
A6202, Revision 1, dated January 4, 1996, are applicable to engines
installed on Boeing 727 series aircraft as well.
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 an uncontained engine failure. This AD requires
a borescope inspection of engines, identified by serial number (S/N)
that were ultrasonically inspected in accordance with AD 96-23-14 with
defective probes. In addition, this AD requires a functional check at
PW of all ultrasonic inspection probes that were overhauled, repaired,
or otherwise altered since original manufacture and not subsequently
functionally checked. The borescope inspection is required to be
accomplished in accordance with the 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 98-ANE-04-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.
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:
98-04-39 Pratt & Whitney: Amendment 39-10351. Docket 98-ANE-04-AD.
Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -
7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan
engines, with combustion chamber outer case (CCOC) part numbers (P/
Ns) 490547, 542155, 616315, 728829, 728829-001, 730413, 730413-001,
730414, 730414-001, 767197, 767279, 767279-001 installed. These
engines are installed on but not limited to Boeing 737 and 727
series, and McDonnell Douglas DC-9 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 (c) of this AD. The request should include an assessment
of the effect 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 uncontained engine failure, inflight engine shutdown,
engine cowl release, and airframe damage, accomplish the following:
(a) For engines identified by serial number (S/N) in Table 1 of
this AD, perform a one-time borescope inspection of the CCOC rear
flange in accordance with paragraph 2.A.(5) of PW Alert Service
Bulletin (ASB) No. A6202, Revision 1, dated January 4, 1996, as
follows:
[[Page 9407]]
Table 1
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648796......... 653799 655969 665370 674333 695297 702602
648859......... 653876 655987 665372 674370 696555 702648
649077......... 653904 656036 665382 674513 696573 702699
649135......... 654043 656084 665393 674564 696645 702712
649157......... 654115 656121 665520 674580 696668 702772
649212......... 654428 656948 665529 674611 696757 707158
649262......... 654557 656964 665744 687407 700037 707200
649331......... 654804 657064 665992 687457 700053 707405
649354......... 654860 657119 666004 687634 700103 707922
649406......... 654877 657386 666019 687851 700140 708332
649451......... 654915 657418 666076 687891 700145 708921
649675......... 654949 657584 666331 687893 700156 709002
653316......... 654986 657613 666682 688029 700223 709168
653329......... 655108 657677 666715 688051 700243 709209
653363......... 655310 657739 666948 688054 700248
653495......... 655437 665410 667042 688103 700261
653514......... 655821 665412 667045 688161 700334
653545......... 655842 665461 667059 688470 700383
653574......... 655857 665468 667068 688491 700398
653609......... 655870 665489 667110 688499 700404
653622......... 655898 665497 674193 689934 700665
653789......... 655900 665364 674251 695290 700133
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(1) For engines installed on McDonnell Douglas DC-9 series
aircraft, inspect within 1,000 cycles in service (CIS) since the
last ultrasonic inspection of the CCOC rear flange performed in
accordance with AD 96-23-14, or within 100 CIS after the effective
date of this AD, whichever occurs later.
(2) For engines installed on Boeing 737 series aircraft, inspect
within 1,500 CIS since the last ultrasonic inspection of the CCOC
rear flange performed in accordance with AD 96-23-14, or within 100
CIS after the effective date of this AD, whichever occurs later.
(3) For engines installed on Boeing 727 series aircraft, inspect
within 2,500 CIS since the last ultrasonic inspection of the CCOC
rear flange performed in accordance with AD 96-23-14, or within 100
CIS after the effective date of this AD, whichever occurs later.
(b) If the ultrasonic probe assembly, PWA 47942, used to inspect
the CCOC rear flange in accordance with AD 96-23-14 was overhauled,
repaired, or otherwise altered since original manufacture and not
subsequently functionally checked at PW, within 30 days after the
effective date of this AD return ultrasonic probes to PW to perform
a functional check of the ultrasonic probe assembly.
Note 2: Operators should note that future inspections performed
using the probe must be performed with a probe that has passed a
functional check at PW since overhaul, repair, or alteration.
(1) If the ultrasonic probe assembly does not pass the
functional check, PW must inform the operator, within 24 hours after
the probe fails the functional check.
(2) If the ultrasonic probe assembly does not pass the
functional check at PW, all engines that were ultrasonically
inspected with that probe in accordance with AD 96-23-14 must be
borescope inspected in accordance with paragraph 2.A.(5) of PW ASB
No. A6202, Revision 1, dated January 4, 1996. Perform the
inspections as follows:
(i) For engines installed on McDonnell Douglas DC-9 series
aircraft, inspect within 1,000 cycles in service (CIS) since the
last ultrasonic inspection of the CCOC rear flange performed in
accordance with AD 96-23-14, or within 100 CIS after determining the
probe is defective, whichever occurs later.
(ii) For engines installed on Boeing 737 series aircraft,
inspect within 1,500 CIS since the last ultrasonic inspection of the
CCOC rear flange performed in accordance with AD 96-23-14, or within
100 CIS after determining the probe is defective, whichever occurs
later.
(iii) For engines installed on Boeing 727 series aircraft,
inspect within 2,500 CIS since the last ultrasonic inspection of the
CCOC rear flange performed in accordance with AD 96-23-14, or within
100 CIS after determining the probe is defective, whichever occurs
later.
(c) 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.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following PW ASB:
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Document No. Pages Revision Date
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A6202.............................. 1-10 1............................... Jan. 4, 1996.
11 Original........................ Feb. 20, 1995.
NDIP-835........................... 1-17 A............................... Oct. 7, 1995.
Total pages: 28.
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This incorporation by reference of Pratt & Whitney Alert Service
Bulletin No. A6202, Revision 1, dated January 4, 1996, was approved
previously by the Director of the Federal Register as of January 2,
1997 (61 FR 63707, December 2, 1996). 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 Regional 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.
(f) This amendment becomes effective on February 25, 1998.
[[Page 9408]]
Issued in Burlington, Massachusetts, on February 11, 1998.
James C. Jones,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-4408 Filed 2-24-98; 8:45 am]
BILLING CODE 4910-13-U
