[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Proposed Rules]
[Pages 6888-6890]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3669]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-48-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This notice revises an earlier proposed airworthiness 
directive (AD), applicable to Pratt & Whitney JT8D series turbofan 
engines, that would have required revisions to the Time Limits Section 
(TLS) of the manufacturer's Engine Manuals (EMs) to include required 
enhanced inspection of selected critical life-limited parts at each 
piece-part exposure. This proposal would modify the airworthiness 
limitations section of the manufacturer's manual and an air carrier's 
approved continuous airworthiness maintenance program to incorporate 
additional inspection requirements. An FAA study of in-service events 
involving uncontained failures of critical rotating engine parts 
indicated the need for mandatory inspections. The mandatory inspections 
are needed to identify those critical rotating parts with conditions, 
which if allowed to continue in service, could result in uncontained 
failures. This action revises the proposed rule by correcting the 
applicability to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -
9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan 
engines, installed on but not limited to Boeing 727 and 737 series, and 
McDonnell Douglas DC-9 series airplanes. The actions specified by this 
proposed AD are intended to prevent critical life-limited rotating 
engine part failure, which could result in an uncontained engine 
failure and damage to the airplane.

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. 98-ANE-48-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 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.

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 notice 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-ANE-48-AD.'' The postcard will be date stamped and 
returned to the commenter.

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. 98-ANE-48-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to supersede airworthiness directive (AD) 2000-21-08, 
Amendment 39-11940 (65 FR 65731, November 2, 2000), applicable to JT8D 
engines, was published as a notice of proposed rulemaking (NPRM) in the 
Federal Register on January 7, 2002 (67 FR 697). That NPRM would have 
required revisions to the Time Limits Section (TLS) of the 
manufacturer's Engine Manuals (EMs) to include required enhanced 
inspection of selected critical life-limited parts at each piece-part 
exposure. An FAA study of in-service events involving uncontained 
failures of critical rotating engine parts indicated the need for 
mandatory inspections. The mandatory inspections are needed to identify 
those critical rotating parts with conditions, which if allowed to 
continue in service, could result in uncontained failures. The actions 
specified by this proposed AD are intended to prevent critical life-
limited rotating engine part failure, which could

[[Page 6889]]

result in an uncontained engine failure and damage to the airplane.
    Since the issuance of that NPRM, the FAA discovered that the 
Applicability Section of the proposal was incorrect. This Supplmental 
NPRM corrects that error. The correct applicability is as follows: 
Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, 
-15A, -17, -17A, -17R, and -17AR series turbofan engines, installed on 
but not limited to Boeing 727 and 737 series, and McDonnell Douglas DC-
9 series airplanes.
    Since this change expands the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Economic Analysis

    The FAA estimates that 5821 engines installed on airplanes of US 
registry would be affected by this proposed AD, that it would take 
approximately 8 work hours per engine to perform the enhanced 
inspection for the first stage HP turbine disks. The average labor rate 
is $60 per work hour. The cost impact of the added inspections per 
engine is approximately $480 per year, with the approximate total cost 
for the US fleet of $2,794,080 per year.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 39-11940 (65 FR 
65731, November 2, 2000 and by adding a new airworthiness directive, to 
read as follows:

Pratt & Whitney: Docket No. 98-ANE-48-AD: Supersedes AD 2000-21-08, 
Amendment 39-11940.

    Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -
7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 
turbofan engines, installed on but not limited to Boeing 727 and 737 
series, and McDonnell Douglas DC-9 series airplanes.

    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 already done.
    To prevent critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, accomplish the following:

Inspections

    (a) Within the next 30 days after the effective date of this AD, 
revise the Time Limits Section (TLS) of the JT8D-1, -1A, -1B, -7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR 
Turbofan Engine Manual, part number, 481672, and for air carrier 
operations revise the approved continuous airworthiness maintenance 
program, by adding the following:
    ``Critical Life Limited Part Inspection
    A. Inspection Requirements:
    (1) This section has the definitions for individual engine piece 
parts and the inspection procedures which are necessary when these 
parts are removed from the engine.
    (2) It is necessary to do the inspection procedures of the piece 
parts in paragraph B when:
    (a) The part is removed from the engine and disassembled to the 
level specified in paragraph B and
    (b) The part has accumulated more than 100 cycles since the last 
piece part inspection, provided that the part was not damaged or 
related to the cause for its removal from the engine.
    (3) The inspections specified in this paragraph do not replace 
or make not necessary other recommended inspections for these parts 
or other parts.
    B. Parts Requiring Inspection:

    Note: Piece part is defined as any of the listed parts with all 
the blades removed.


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             Description                       Section                 Inspection
----------------------------------------------------------------------------------------
Hub (Disk), 1st Stage Compressor:
    Hub Detail--All P/N's...........  72-33-31                  -02, -03, -04
    Hub Assembly--All P/N's.........  72-33-31                  -02, -03, -04
2nd Stage Compressor:
    Disk--All P/N's.................  72-33-33                  -02
    Disk Assembly--All P/N's........  72-33-33                  -02
    Disk, 13th Stage Compressor: All  72-36-47                  -02
     P/N's.
    HP Turbine Disk, First Stage w/   72-52-04                  -03
     integral Shaft: All P/N's.
HP Turbine, First Stage, w/
 Separable shaft:
    Rotor Assembly--All P/N's.......  72-52-02                  -04
    Disk--All P/N's.................  72-52-02                  -03
Disk, 2nd Stage Turbine: All P/N's..  72-53-16                  -02
Disk, 3rd Stage Turbine: All P/N's..  72-53-17                  -02
Disk (Separable), 4th Stage Turbine:  72-53-15                  -02
 All P/N's.
Disk (Integral Disk/Hub), 4th Stage   72-53-18                  -02''
 Turbine: All P/N's.
----------------------------------------------------------------------------------------------------------------


[[Page 6890]]

    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
must be performed using the TLS of the PW JT8D-200 Turbofan Engine 
Manual.

Alternative Methods of Compliance

    (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 Engine Certification Office (ECO). Operators 
shall submit their requests through an appropriate FAA Principal 
Maintenance Inspector (PMI), who may add comments and then send it 
to the 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

    (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 airplane to a location where 
the requirements of this AD can be accomplished.

Continuous Airworthiness Maintenance Program

    (e) FAA-certificated air carriers that have an approved 
continuous airworthiness maintenance program in accordance with the 
record keeping requirement of Sec. 121.369 (c) of the Federal 
Aviation Regulations (14 CFR 121.369 (c)) of this chapter must 
maintain records of the mandatory inspections that result from 
revising the TLS of the PW JT8D/09200 Turbofan Engine Manual, and 
the air carrier's continuous airworthiness program. Alternatively, 
certificated air carriers may establish an approved system of record 
retention that provides a method for preservation and retrieval of 
the maintenance records that include the inspections resulting from 
this AD, and include the policy and procedures for implementing this 
alternate method in the air carrier's maintenance manual required by 
Sec. 121.369 (c) of the Federal Aviation Regulations (14 CFR 121.369 
(c)); however, the alternate system must be accepted by the 
appropriate PMI and require the maintenance records be maintained 
either indefinitely or until the work is repeated. Records of the 
piece-part inspections are not required under Sec. 121.380 (a) (2) 
(vi) of the Federal Aviation Regulations (14 CFR 121.380 (a) (2) 
(vi)). All other operators must maintain the records of mandatory 
inspections required by the applicable regulations governing their 
operations.

    Note 3: The requirements of this AD have been met when the 
engine manual changes are made and air carriers have modified their 
continuous airworthiness maintenance plans to reflect the 
requirements in the PW JT8D-200 Turbofan Engine Manual.


    Issued in Burlington, Massachusetts, on February 7, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-3669 Filed 2-13-02; 8:45 am]
BILLING CODE 4910-13-P