[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]
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