[Federal Register Volume 61, Number 232 (Monday, December 2, 1996)]
[Rules and Regulations]
[Pages 63707-63709]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-30127]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-ANE-79; Amendment 39-9820; AD 96-23-14]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes two existing airworthiness
directives (ADs), applicable to Pratt & Whitney (PW) JT8D series
turbofan engines, that currently require repetitive eddy current,
fluorescent penetrant, fluorescent magnetic penetrant, or visual
inspections for cracks in the rear flange, and ultrasonic, fluorescent
penetrant, or fluorescent magnetic penetrant inspections for cracks in
the PS4 boss, and drain bosses of the
[[Page 63708]]
combustion chamber outer case (CCOC); and an additional inspection of
the CCOC rear flange for intergranular cracking. This amendment
requires reducing the rear flange inspection interval for CCOCs when
only the aft face of the rear flange has been inspected, and
introducing an improved ultrasonic probe assembly. In addition, this
amendment introduces a rotating eddy current probe for shop inspections
in which the case is removed from the engine. Also, this amendment
eliminates fluorescent penetrant inspection (FPI), fluorescent magnetic
particle inspection (FMPI), and visual inspections from hot section
disassembly level inspection procedures. This amendment is 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 CCOC's
that were mandated in the current ADs. The actions specified by this AD
are intended to prevent uncontained engine failure, inflight engine
shutdown, engine cowl release, and airframe damage.
DATES: Effective January 2, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 2, 1997.
ADDRESSES: 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 Federal Aviation Administration (FAA), New England
Region, Office of the Assistant Chief Counsel, 12 New England Executive
Park, Burlington, MA 01803-5299; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Robert E. Guyotte, Manager, Engine
Certification Branch, Engine Certification Office, FAA, Engine and
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803-5299; telephone (617) 238-7142, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding airworthiness
directive (AD) 87-11-07 R1, Amendment 39-6360 (54 FR 46045, November 1,
1989), which is applicable to Pratt & Whitney (PW) JT8D series turbofan
engines, was published in the Federal Register on March 15, 1994 (59 FR
11942). That action proposed to require to reduce the inspection
interval in AD 87-11-07 R1 for combustion chamber outer cases (CCOCs)
that have had only the aft face of the rear flange inspected and
introduced an improved ultrasonic probe assembly.
On May 22, 1996 (61 FR 28114, June 4, 1996), the Federal Aviation
Administration (FAA) issued a Supplementary NPRM, that revised the
earlier NPRM by proposing to simplify the compliance instructions and
incorporate a new PW Alert Service Bulletin (ASB). That Supplemental
NPRM also revised the earlier NPRM by introducing new non-destructive
inspection procedures (NDIPs), and introducing a rotating eddy current
probe for shop inspections in which the case is removed from the
engine. In addition, the Supplemental NPRM eliminated fluorescent
penetrant inspection (FPI), fluorescent magnetic particle inspection
(FMPI), and visual inspections from hot section disassembly level
inspection procedures. The Supplemental NPRM also revised the earlier
NPRM by consolidating the inspection requirements of an additional
current AD, 95-08-15, into the proposed AD.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter states that the effective date for the borescope
inspection required by paragraph (a) of this AD should be the same as
the effective date of AD 95-08-15. The proposed AD would supersede AD
95-08-15, therefore the borescope inspection intervals have already
been initiated to comply with AD 95-08-15. The FAA concurs. The FAA has
revised the accomplishment effective date in this final rule from the
effective date of this AD to May 9, 1995, which is the effective date
of AD 95-08-15.
One commenter states that the PW JT8D-7B engine model was omitted
from the applicability section of the proposed rule, but was included
in the ADs to be superseded. The FAA concurs and has revised this final
rule accordingly.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 6,815 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take approximately
4.5 work hours per engine to accomplish the required actions, and that
the average labor rate is $60 per work hour. Based on these figures,
the total cost impact of the AD on U.S. operators is estimated to be
$1,840,050.
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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-6360 (54 FR
46045, November 1, 1989) and amendment 39-9204 (60 FR 20019, April 24,
1995), and by adding a new
[[Page 63709]]
airworthiness directive, Amendment 39-9820, to read as follows:
96-23-14 Pratt & Whitney: Amendment 39-9820. Docket 93-ANE-79.
Supersedes AD 87-11-07 R1, Amendment 39-6360, AD 87-11-07, Amendment
39-5619, and AD 95-08-15, Amendment 39-9204.
Applicability: Pratt & Whitney (PW) Models 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 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 CCOC flange cracks that could result in uncontained
engine failure, inflight engine shutdown, engine cowl release, and
airframe damage, accomplish the following:
(a) Inspect, disposition, and report CCOC distress, in
accordance with the intervals and procedures described in Paragraphs
2.A and 2.C of PW Alert Service Bulletin (ASB) No. A6202, Revision
1, dated January 4, 1996. Reporting requirements have been approved
by the Office of Management and Budget and assigned OMB control
number 2120-0056.
(1) For the purposes of this AD, the accomplishment effective
date to be used for determination of inspection intervals, as
required by Section 2.A of PW ASB A6202, Revision 1, dated January
4, 1996, is defined as May 9, 1995, which is the effective date of
AD 95-08-15.
(b) Inspect, disposition ,and report CCOC distress in accordance
with the intervals and procedures described in Paragraphs 2.A. (Part
I), 2.B. (Part II), and 2.D of PW ASB No. A6228, dated November 7,
1995. Reporting requirements have been approved by the Office of
Management and Budget and assigned OMB control number 2120-0056.
(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. 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 method of compliance with this AD, if any, may be
obtained from the Engine Certification Office.
(d) 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 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 Pratt & Whitney ASBs and NDIP documents:
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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.
A6228............................... 1-31 Original....................... Nov. 7, 1995.
NDIP-620............................ 1-15 A.............................. Oct. 7 1995.
NDIP-691............................ 1-20 B.............................. Oct. 7, 1995.
NDIP-781............................ 1-21 Original....................... Oct. 7, 1995.
NDIP-795............................ 1-20 Original....................... Oct. 7, 1995.
NDIP-829............................ 1-14 Original....................... Oct. 7, 1995.
NDIP-834............................ 1-19 A.............................. Oct. 7, 1995.
NDIP-856............................ 1-42 Original....................... Oct. 7, 1993.
Total pages: 182.
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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.
(f) This amendment becomes effective on January 2, 1997.
Issued in Burlington, Massachusetts, on November 7, 1996.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 96-30127 Filed 11-29-96; 8:45 am]
BILLING CODE 4910-13-U
