[Federal Register Volume 61, Number 232 (Monday, December 2, 1996)]
[Rules and Regulations]
[Pages 63706-63707]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-30096]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-ANE-02; Amendment 39-9821; AD 96-23-15]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-200 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, 
that currently requires periodic inspection of fan blades for locked 
rotors and foreign object damage (FOD), unlocking of shrouds if 
necessary, lubrication of fan blade shrouds, and dimensional 
restoration of the fan blade leading edge. This amendment adds a 
requirement to install improved design fan blades as terminating action 
for the inspections. This amendment is prompted by the introduction 
into service of improved design fan blades. The actions specified by 
this AD are intended to prevent fan blade failure, which can result in 
damage to the aircraft.

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, Publication Department, Supervisor 
Technical Publications Distribution, M/S 132-30, 400 Main St., East 
Hartford, CT 06108; telephone (860) 565-7700, 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: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (617) 238-
7134, 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) 95-12-19, Amendment 39-9270 (60 FR 31388, June 15, 
1995), applicable to certain Pratt & Whitney (PW) JT8D-200 series 
turbofan engines, was published in the Federal Register on May 6, 1996 
(61 FR 20194). That action proposed to add a requirement to install 
improved design fan blades as terminating action for the periodic 
inspection of fan blades for locked rotors and foreign object damage 
(FOD), unlocking of shrouds if necessary, lubrication of fan blade 
shrouds, and dimensional restoration of the fan blade leading edge. The 
action would be required to be accomplished in accordance with PW Alert 
Service Bulletin (ASB) No. A6241, dated January 25, 1996.
    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 rule as proposed.
    One commenter concurs with the inspection and maintenance 
provisions of the proposed AD. However, the commenter questions the 
proposed compliance schedule for the terminating action to incorporate 
the new fan blades. The compliance schedule is based on fan blade 
cycles in service (CIS). The commenter states that since (1) the fan 
blade fractures are due to a high cycle fatigue (HCF) failure mode that 
is not linked to total part CIS on the fan blade, and (2) that 
individual fan blade CIS are currently not tracked, an alternative 
compliance requirement based on completing a specific yearly percentage 
rate of the operator's engine sets would be less burdensome to the 
operators. The FAA concurs in part. When the FAA assessed the risk, the 
FAA based the compliance schedule on total part CIS. It has been the 
FAA's practice to define intervals for corrective action in an AD by 
means of part CIS. Monitoring this program on a fleet-wide basis using 
the suggested percentage rate would not provide the FAA with an 
adequate means to ensure that blades were removed before becoming a 
safety problem. Individual operators, however, may request such a 
percentage-based program that includes those assurances as an 
alternative method of compliance to the AD. The FAA, therefore, does 
not concur that the proposed AD should be revised.
    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 as proposed.
    The FAA estimates that 1,100 engines installed on aircraft of U.S. 
registry will be affected by this AD, that it will take approximately 
19 work hours per engine to accomplish the required actions, and

[[Page 63707]]

that the average labor rate is $60 per work hour. The FAA also 
estimates that the parts modification will cost $1,020 per engine, 
which includes a manufacturer's discount of $1,700 per engine. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $2,376,000.
    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. Sec. 39.13 is amended by removing Amendment 39-9270 (60 FR 
31388, June 15, 1995) and by adding a new airworthiness directive, 
Amendment 39-9821, to read as follows:
96-23-15  Pratt & Whitney: Amendment 39-9821. Docket 96-ANE-02. 
Supersedes AD 95-12-19, Amendment 39-9270.

    Applicability: Pratt & Whitney (PW) Models JT8D-209,-217, -217A, 
-217C, and -219 turbofan engines that have not incorporated PW 
Service Bulletin (SB) No. 6193, dated October 31, 1994, or with fan 
blade, Part Numbers (P/N's) 798821, 798821-001, 808121, 808121-001, 
809221, 811821, 851121, 851121-001, 5000021-02, 5000021-022, and 
5000021-032 installed. These engines are installed on but not 
limited to McDonnell Douglas MD-80 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 (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 eliminated, the request should include specific 
proposed actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fan blade failure, which can result in damage to the 
aircraft, accomplish the following:
    (a) Inspect fan blades and shrouds, unlock fan blade shrouds, 
lubricate fan blade shrouds, restore leading edge dimensions, and 
modify or install improved design fan blades in accordance with the 
schedule and procedures described in Parts 1, 2, and 3 of the 
Accomplishment Instructions of PW Alert Service Bulletin (ASB) No. 
A6241, dated January 25, 1996.
    (b) Modification of fan blades to the improved design 
configuration or installation of improved design fan blades in 
accordance with Part 3 of the Accomplishment Instructions of PW ASB 
No. A6241, dated January 25, 1996, constitutes terminating action to 
the inspections and maintenance actions described in Parts 1 and 2 
of that ASB.
    (c) For the purpose of this AD, the accomplishment effective 
date to be used for determination of compliance intervals, as 
required by Section 2 of PW ASB No. A6241, dated January 25, 1996, 
is defined as the effective date of this AD.
    (d) For the purpose of this AD, ``repair'' as specified in Part 
3, Paragraph A.(1)(b) of the Accomplishment Instructions of PW ASB 
No. A6241, dated January 25, 1996, is defined as the refurbishment 
of fan blades in accordance with Part 3, Paragraph C of the 
Accomplishment Instructions of PW ASB No. A6241, dated January 25, 
1996.
    (e) Alternative methods of compliance that have been approved 
for AD 95-12-19 are applicable for this AD and additional approval 
is not required.
    (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. 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.

    (g) 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.
    (h) The actions required by this AD shall be done in accordance 
with the following Pratt & Whitney ASB:

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              Document No.                 Pages            Revision                          Date              
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A6241...................................    1-14  Original...................  January 25, 1996.                
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    Total pages: 14.
    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, Publication 
Department, Supervisor Technical Publications Distribution, M/S 132-
30, 400 Main St., East Hartford, CT 06108; telephone (860) 565-7700, 
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.
    (i) 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. 96-30096 Filed 11-29-96; 8:45 am]
BILLING CODE 4910-13-U