[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Proposed Rules]
[Pages 6890-6892]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3668]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-32-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Models JT8D-209, -217, 
-217A, -217C and -219 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to 
supersede an existing airworthiness directive (AD), that is applicable 
to Pratt & Whitney JT8D models -209, -217, -217A, -217C and -219 
turbofan engines. That AD currently requires initial and repetitive 
fluorescent magnetic particle inspections or fluorescent penetrant 
inspections of the combustion chamber outer case (CCOC) for cracks, 
and, if necessary, replacement with serviceable parts. Also, that AD 
requires a one-time boss material verification, and, if necessary, 
replacement with serviceable parts. Finally, that AD requires 
replacement of CCOC's with welded-on bosses with improved, one-piece 
CCOC's. This proposal would require lower initial inspection thresholds 
for all CCOC's installed in any JT8D model -209, -217, -217A, -217C or 
-219 turbofan engine. This proposal is prompted by reports of cracked 
CCOC's that had accumulated fewer cycles in service than the initial 
inspection thresholds required by the current AD. Also, a CCOC part 
number was discovered with incorrect material not identified by serial 
number in PW JT8D ASB 6359. The actions specified by the proposed AD 
are intended to prevent uncontained failure of the CCOC, which could 
cause release of debris, damage to the airplane, or fire.

DATES: Comments must be received by April 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 99-NE-32-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: [email protected]. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in the proposed rule 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, by appointment, at the Federal Aviation Administration (FAA), 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NE-32-AD.'' The postcard will be date stamped and 
returned to the commenter.

[[Page 6891]]

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-NE-32-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    On December 8, 1999, the Federal Aviation Administration (FAA) 
issued airworthiness directive (AD) 99-26-06, Amendment 39-11465 (64 FR 
71280, December 21, 1999), to require initial and repetitive 
fluorescent magnetic particle inspections or fluorescent penetrant 
inspections of the combustion chamber outer case (CCOC) for cracks, 
and, if necessary, replacement with serviceable parts. Also, that AD 
requires a one-time boss material verification, and, if necessary, 
replacement with serviceable parts. Finally, that AD requires 
replacement of CCOC's with welded-on bosses with improved, one-piece 
CCOC's. That action was prompted by a report of an uncontained engine 
failure caused by fatigue cracks originating at the weld joining the 
drain boss to the CCOC. That condition, if not corrected, could result 
in CCOC cracks, which could result in an uncontained engine failure and 
damage to the airplane.
    Since that AD was issued, the FAA has received reports of cracked 
CCOC's that had accumulated fewer cycles in service than the initial 
inspection thresholds defined in PW JT8D ASB 6359. Also, a CCOC part 
number (P/N), 797707, was found with incorrect material that was not 
identified by serial number in PW ASB JT8D ASB 6359. As a result, PW 
JT8D ASB 6359 was revised on July 31, 2000, to lower the initial 
inspection threshold from 15,000 cycles in service (CIS) for P/N 
500238-01; 18,000 CIS for all other P/N's installed in JT8D-209, -217, 
-217A, and -217C engines; and 15,000 CIS for all other P/N's installed 
in JT8D-219 engines to 12,000 CIS for all P/N's installed in any 
engine. Also, the revision to PW ASB JT8D ASB A6359 expands the serial 
number list of P/N 797707 cases to include all CCOC's manufactured with 
that part number. Some minor editorial revisions to PW JT8D ASB A6359, 
Revision 1, were subsequently made on August 31, 2001. PW JT8D SB 6291, 
Revision 2, was also revised to reflect the lower thresholds for 
inspection and replacement of CCOC's.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of PW JT8D 
ASB No. A6359, Revision 2, dated July 31, 2000; and PW JT8D ASB A6359, 
Revision 3, dated August 31, 2001, that describe procedures and 
intervals for inspecting CCOC's for cracks and incorrect material, and 
PW Service Bulletin (SB) No. 6291, Revision 3, dated August 31, 2001, 
that describes procedures for installation of CCOC P/N 815556.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Pratt & Whitney JT8D models -209, -217, -
217A, -217C and -219 turbofan engines of this same type design, the 
proposed AD would supersede AD 99-26-06 to require, for PW models JT8D-
209, -217, -217A, -217C and -219 engines, inspections and replacement 
of CCOC's at the lower inspection thresholds and the expanded serial 
number lists outlined in PW JT8D ASB 6359, Revision 3, dated August 31, 
2001; and SB 6291, Revision 2, dated August 31, 2001. The actions are 
required to be done in accordance with the service bulletins described 
previously.

Economic Analysis

    There are approximately 2,624 engines of the affected design in the 
worldwide fleet. The FAA estimates that 1,280 engines installed on 
airplanes of U.S. registry are affected by the current AD and that 
number would remain the same under this proposed AD. The FAA also 
estimates that it takes approximately 2.5 work hours per engine to 
accomplish the required inspections, that the average labor rate is $60 
per work hour, and those estimates would not change for the proposed 
AD. The cost of the required parts has increased since the current AD 
was issued, and would now cost approximately $46,910 per engine. Based 
on these figures, the updated total cost impact of the proposed 
superseding AD on U.S. operators is estimated to be $60,236,800.

Regulatory Analysis

    This proposed rule does not have federalism implications, as 
defined in Executive Order 13132, because it would not have a 
substantial direct effect 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 39-11465, (64 FR 
71280), and by adding a new airworthiness directive:

Pratt & Whitney: Docket No. 99-NE-32-AD. Supersedes AD 99-26-06, 
Amendment 39-11465.

Applicability

    This airworthiness directive (AD) is applicable to Pratt & 
Whitney (PW) models JT8D-209, -217, -217A, -217C, and -219 turbofan 
engines with combustion chamber outer case (CCOC), part numbers (P/
N's) 5000238-01, 797707, 807684, and 815830 installed. These engines 
are installed on but not limited to McDonnell Douglas MD-80 series 
airplanes.

    Note 1: This 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 (f) 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

[[Page 6892]]

eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent uncontained failure of the CCOC, which could cause 
release of debris, damage to the airplane, or fire, do the 
following:

Inspections

    (a) Perform initial and repetitive fluorescent magnetic particle 
inspections (FMPI) or fluorescent penetrant inspections (FPI) of 
drain bosses and Ps4 bosses of the CCOC for cracks, and, if 
necessary, replace with serviceable parts before further flight, in 
accordance with the procedures and intervals specified in paragraph 
1.A. of the Accomplishment Instructions of PW JT8D Alert Service 
Bulletin (ASB) A6359, Revision 3, dated August 31, 2001.
    (b) For all CCOC's P/N 797707 inspect for proper Ps4 and drain 
boss material, and, if necessary, replace with serviceable parts 
before further flight, in accordance with the procedures and 
intervals specified in paragraph 1.B. of the Accomplishment 
Instructions of PW JT8D ASB A6359, Revision 3, dated August 31, 
2001.

Effective Date for Computing Compliance Intervals

    (c) Use the effective date of this AD for computing compliance 
intervals whenever PW JT8D ASB A6359, Revision 3, dated August 31, 
2001, refers to the publication date of the ASB.

Terminating Action

    (d) At the next part accessibility after the effective date of 
this AD when the CCOC has accumulated cycles-in-service greater than 
the initial inspection threshold specified in Table 1 of PW JT8D ASB 
A6359, Revision 3, dated August 31, 2001, replace the CCOC with a 
one-piece machined CCOC assembly, P/N 815556, in accordance with PW 
JT8D Service Bulletin (SB) 6291, dated May 20, 1997, or Revision 1 
dated July 9, 1997, or Revision 2, dated August 27,1999, or Revision 
3 dated August 31, 2001. Installation of an improved, one-piece 
CCOC, P/N 815556, constitutes terminating action to the inspections 
required by this AD.

Definition

    (e) For the purpose of this AD, part accessibility is defined as 
an engine disassembly in which the CCOC is removed from the engine.

Alternative Methods of Compliance

    (f) 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 (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (g) 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 airplane to a location where the 
requirements of this AD can be done.

    Issued in Burlington, Massachusetts, on February 7, 2002.
Francis A Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-3668 Filed 2-13-02; 8:45 am]
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