AD Amdt-39-10351

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-4408]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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: ``<a href="/cdn-cgi/l/email-protection#c9f0e4a8ade4c3aca7aea0a7acb9bba6b989afa8a8e7ada6bde7aea6bf">9-ad-
<span class="__cf_email__" data-cfemail="d3b6bdb4babdb6a3a1bca393b5b2b2fdb7bca7fdb4bca5">[email&#160;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 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                                                    
----------------------------------------------------------------------------------------------------------------
                                                                                                                
----------------------------------------------------------------------------------------------------------------
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                  
----------------------------------------------------------------------------------------------------------------

    (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:

----------------------------------------------------------------------------------------------------------------
            Document No.                 Pages                 Revision                          Date           
----------------------------------------------------------------------------------------------------------------
A6202..............................       1-10     1...............................  Jan. 4, 1996.              
                                            11     Original........................  Feb. 20, 1995.             
NDIP-835...........................       1-17     A...............................  Oct. 7, 1995.              
    Total pages: 28.                                                                                            
----------------------------------------------------------------------------------------------------------------

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