[Federal Register Volume 64, Number 136 (Friday, July 16, 1999)]
[Rules and Regulations]
[Pages 38299-38301]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-17555]



[[Page 38299]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-31-AD; Amendment 39-11221; AD 99-15-02]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Pratt & Whitney (PW) JT9D series turbofan 
engines, that requires initial and repetitive in-shop eddy current and 
on-wing ultrasonic inspections of the Combustion Chamber Outer Casing 
(CCOC) forward flange (L-flange) fillet radius for cracking, and 
replacing cracked L-flanges with serviceable parts. Replacement with an 
improved L-flange constitutes terminating action to the repetitive 
inspections. This amendment is prompted by reports of CCOC rupture due 
to cracking in the L-flange fillet radius. The actions specified by the 
proposed AD are intended to prevent CCOC rupture due to cracking, which 
could result in an uncontained engine failure and damage to the 
aircraft.

DATES: Effective date August 16, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 16, 1999.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-8770, fax (860) 565-4503. This information may be 
examined at the Federal Aviation Administration (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: Peter White, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7128, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Pratt & Whitney (PW) JT9D 
series turbofan engines was published in the Federal Register on 
December 21, 1998 (63 FR 70352). That action proposed to require 
initial and repetitive in-shop eddy current and on-wing ultrasonic 
inspections of the Combustion Chamber Outer Casing (CCOC) forward 
flange (L-flange) fillet radius for cracking, and replacing cracked L-
flanges with serviceable parts.
    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 supports the proposed actions contained in the notice 
of proposed rulemaking (NPRM).
    One commenter notes that the aircraft applicability may be 
incorrect because it includes the A300 Aircraft. The commenter believes 
that the JT9D-7R4 is the only model being installed on the A300 and 
that the service bulletin (SB) may be incorrect. The commenter is 
correct. Pratt & Whitney indicates that the JT9D-3/-20 models were 
never installed on the A300 Aircraft, and that the documents referenced 
are in error. The Applicability paragraph has been changed accordingly. 
The listing of aircraft installations in an AD that applies to engines, 
however, is informative only and does not affect the applicability of 
the AD to the identified engine models.
    One commenter notes that Chromalloy makes a replacement CCOC under 
a supplemental type certificate (STC) P/N CFL758479, that the FAA 
should consider as acceptable terminating action to the AD. The 
commenter also states that Chromalloy makes a replacement CCOC L-flange 
under a parts manufacturing approval (PMA) which the commenter claims 
is the equivalent to the flange introduced by PW SB 4482, and should 
also be considered as acceptable terminating action for the AD. The FAA 
agrees. These part numbers have been added to the list of parts whose 
installation will constitute terminating actions to the AD in a new 
paragraph (e).
    One commenter utilizes Standard Practice Operating Procedure (SPOP) 
82 florescent penetrant inspection (FPI) of the L-flange when the part 
is in their shop. For cases that have used SPOP 82 FPI at last shop 
visit, the commenter requests that the FAA extend the 250 cycle limit 
to the 500 cycle limit for the initial on-wing inspection. The FAA does 
not agree. The performance of SPOP 82, when compared to the required 
ultrasonic inspection, does not raise the probability of detecting a 
crack sufficiently to increase the initial inspection requirement from 
250 cycles to 500 cycles.
    One commenter requested that the effective date of the AD be 
changed from 30 days after publication in the Federal Register to 60 
days. The commenter states that he often receives the ADs weeks after 
their publication date, leaving little time to update his tracking 
system. The FAA does not agree. All AD's are published in the Federal 
Register and are available on a subscription basis from the Government 
Printing Office within days of publication. In addition, all ADs are 
available on the Federal Register's Internet web site the day they are 
published and are listed on the Federal Register's preview web site the 
day before publication. Additionally, the FAA mails hard copies of ADs 
to all registered owner/operators within a week of their publication in 
the Federal Register.
    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 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.

[[Page 38300]]

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:

99-15-02 Pratt & Whitney: Amendment 39-11221. Docket 98-ANE-31-AD.

    Applicability: Pratt & Whitney (PW) JT9D-3A, -7, -7H, -7A, -7AH, 
-7F, -7J, -20, and -20J series turbofan engines, with Combustion 
Chamber Outer Casing (CCOC), part numbers (P/Ns) 644801, 693294, 
709016, 729237, 729238, and 729239, installed. These engines are 
installed on but not limited to certain models of Boeing 747 and 
McDonnell Douglas DC-10 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 (h) 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 rupture due to cracking, which could result in 
an uncontained engine failure and damage to the aircraft, accomplish 
the following:
    (a) Perform initial on-wing ultrasonic inspections of the CCOC 
forward flange (L-flange) fillet radius for cracking in accordance 
with PW Alert Service Bulletin (ASB) No. A6343 Revision 1, dated 
October 8, 1998, as follows:
    (1) For engines that have not had the L-flange fillet radius 
eddy current inspected using the JT9D Engine Manual (P/N 646028, P/N 
770407, P/N 770408, as appropriate) Revision No. 104; or Temporary 
Revision No. 72-6517, Temporary Revision No. 72-6334, or Temporary 
Revision No. 72-6206, all of which were superseded by manual 
Revision No. 104; at the last shop visit, inspect within 250 cycles 
in service (CIS) after the effective date of this AD, or the next 
shop visit, whichever occurs first.
    (2) For engines that did have the L-flange fillet radius eddy 
current inspected using the JT9D Engine Manual (P/N 646028, P/N 
770407, P/N 770408, as appropriate) Revision No. 104; or Temporary 
Revision No. 72-6517, Temporary Revision No. 72-6334, or Temporary 
Revision No. 72-6206, all of which were superseded by manual 
Revision No. 104; at the last shop visit, inspect within 2,000 CIS, 
or the next shop visit after the effective date of this AD, 
whichever occurs first.
    (b) Thereafter, ultrasonically inspect on-wing at intervals not 
to exceed 500 CIS since last on-wing inspection in accordance with 
PW Alert Service Bulletin (ASB) No. A6343 Revision 1, dated October 
8, 1998, or 2000 cycles in service (CIS) since last in-shop ECI 
inspection, whichever occurs later.
    (c) If a crack is found during on-wing inspection, remove the 
part from service, and replace with a serviceable part as follows:
    (1) For cracks found to be over the inspection threshold limit, 
but less than 2 inches, remove within 5 CIS.
    (2) For cracks found to be over the inspection threshold limit 
and equal to or greater than 2 inches, remove prior to further 
flight.
    (d) If a crack in the L-flange fillet radius of the CCOC is 
found during in-shop inspection, remove the CCOC and replace with a 
serviceable part or replace the L-flange with an improved L-flange 
P/N 734515 or 056-1133-1 in accordance with the accomplishment 
instructions of PW ASB No. 6343 Revision 1, dated October 8, 1998.
    (e) Installation of CCOC's containing improved L-flange P/N's 
734515 or 056-1133-1, or installation of CCOC's with P/N's 758479 or 
CFL758479, constitute terminating action to the repetitive 
inspection requirements of this AD.
    (f) Inspect the CCOC L-flange fillet radius during every CCOC 
shop visit in accordance with JT9D Engine Manual (P/N 646028, P/N 
770407, P/N 770408, as appropriate) Revision No. 104 (or Temporary 
Revision No. 72-6517, Temporary Revision No. 72-6334, or Temporary 
Revision No. 72-6206, which were superseded by manual Revision No. 
104); that details eddy current inspection procedures for the L-
flange fillet radius.
    (g) For the purpose of this AD, a shop visit is defined as 
anytime the L-flange is separated in the process of performing 
engine repair.
    (h) 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 request 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.

    (i) 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.
    (j) The inspections must be done in accordance with the 
following Pratt & Whitney SBs:

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         Document No.                Pages                    Revision                           Date
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JT9D A6343....................          1-5     Rev. 1.............................  October 8, 1998.
                                        6-9     Original...........................  July 31, 1998.
                                      10-11     Rev. 1.............................  October 8, 1998.
                                         12     Original...........................  July 31, 1998.
                                         13     Rev. 1.............................  October 8, 1998.
    Total Pages: 13.
4482..........................            1     Rev. 1.............................  July 8, 1976.
                                          2     Original...........................  September 5, 1975.
                                          3     Rev. 1.............................  July 8, 1976.
                                          4     Original...........................  September 5, 1975.
                                          5     Rev. 1.............................  July 8, 1976.
                                        6-8     Original...........................  September 5, 1975.
                                          9     Rev. 1.............................  July 8, 1976.
                                         10     Original...........................  September 5, 1975.
    Total pages: 10.
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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) 565-8770, fax (860) 565-
8770. Copies may be inspected at the FAA, New England Region, Office 
of the Regional Counsel, 12 New

[[Page 38301]]

England Executive Park, Burlington, MA; or at the Office of the 
Federal Register, 800 North Capitol Street, NW, suite 700, 
Washington, DC.
    (k) This amendment becomes effective on August 16, 1999.

    Issued in Burlington, Massachusetts, on July 6, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-17555 Filed 7-15-99; 8:45 am]
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