Document ID: FAA-2009-0317-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Pratt and Whitney JT8D-7, -7A, -7B, -9, -9A, -11, -15, and -17 Turbofan Engines
Posted Date: 2009-08-07T04:00Z

[Federal Register: August 7, 2009 (Volume 74, Number 151)]
[Proposed Rules]               
[Page 39582-39584]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07au09-11]                         

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0317; Directorate Identifier 79-ANE-18]
RIN 2120-AA64

 
Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, 
-9A, -11, -15, and -17 turbofan engines with 2nd stage fan blades, part 
number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402 
installed. That AD currently requires initial and repetitive ultrasonic 
inspection (UI) and fluorescent penetrant inspection (FPI) of those P/N 
2nd stage fan blades. This proposed AD would replace the required FPI 
with eddy current inspection (ECI) on all affected 2nd stage fan blades 
and would maintain the requirement of ultrasonic inspection (UI) of the 
blade root attachment on some of the affected 2nd stage fan blades. 
This proposed AD would also introduce an optional terminating action to 
the repetitive blade inspections for certain engine models. This 
proposed AD results from reports of 10 fractures of 2nd stage fan 
blades since AD 87-14-01R1 became effective. We are proposing this AD 
to prevent uncontained failure of 2nd stage fan blades, which could 
result in damage to the airplane.

DATES: We must receive any comments on this proposed AD by October 6, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

[[Page 39583]]

FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2009-0317; Directorate 
Identifier 79-ANE-18'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    The FAA proposes to amend 14 CFR part 39 by superseding AD 87-14-01 
R1, Amendment 39-6359 (54 FR 43954, October 30, 1989). That AD requires 
initial and repetitive UI and FPI of P/N 433802, 645902, 759902, 
695932, 678102, and 746402 2nd stage fan blades. That AD was the result 
of reports of on-going fractures of 2nd stage fan blades since 1980. 
That condition, if not corrected, could result in uncontained failure 
of 2nd stage fan blades, which could result in damage to the airplane.

Actions Since AD 87-14-01 R1 Was Issued

    Since AD 87-14-01 R1 was issued, Pratt & Whitney has developed and 
published an ECI procedure for inspecting the 2nd stage fan blade pin-
root holes. We have reviewed this procedure and determined that 
mandating this ECI procedure will result in an increased level of 
safety for the affected engines.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For that reason, we are proposing this AD, 
which would require, for 2nd stage fan blades P/Ns 678102 and 746402, 
an ECI of the blade pin-root holes for cracks, and for 2nd stage fan 
blades P/Ns 433802, 645902, 759902, and 695932, an ECI of the blade 
pin-root holes and UI the blade root attachment for cracks. This 
proposed AD would also eliminate the JT8D-1, -1A, and -1B engines from 
the applicability, because those engine models have either been 
converted to other affected engine models included in the proposed AD 
or retired from service.

Costs of Compliance

    We estimate that this proposed AD would affect 1,380 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 25 work-hours per engine to perform one inspection cycle, 
and that the average labor rate is $80 per work-hour. Based on these 
figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $2,760,000.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed AD:
    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. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing Amendment 39-6359 (54 FR 
43954, October 30, 1989) and by adding a new airworthiness directive to 
read as follows:

Pratt & Whitney: Docket No. FAA-2009-0317; Directorate Identifier 
79-ANE-18.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this

[[Page 39584]]

airworthiness directive (AD) action by October 6, 2009.

Affected ADs

    (b) This AD supersedes AD 87-14-01 R1, Amendment 39-6359.

Applicability

    (c) This AD applies to Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 turbofan engines, with 2nd stage fan blades, 
part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, 
installed. These engines are installed on, but not limited to, 
Boeing 727, 737, and McDonnell Douglas DC-9 series airplanes.

Unsafe Condition

    (d) This AD results from reports of 10 fractures of 2nd stage 
fan blades since AD 87-14-01R1 became effective. We are issuing this 
AD to prevent uncontained failure of 2nd stage fan blades, which 
could result in damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

2nd Stage Fan Blade Inspections

    (f) For 2nd stage fan blades, P/N 678102 and P/N 746402, perform 
an eddy current inspection (ECI) of the blade pin-root holes for 
cracks, and for 2nd stage fan blades, P/Ns 433802, 645902, 759902, 
and 695932, perform an ECI of the blade pin-root holes and perform 
an ultrasonic inspection (UI) of the blade root attachment for 
cracks, as follows:
    (1) Perform an inspection at the first disassembly of the 2nd 
stage fan rotor from the low-pressure (LP) compressor after 
accumulation of 3,000 cycles-in-service (CIS) since the last 
inspection of the blade root attachment, not to exceed 10,000 CIS 
since last inspection.
    (2) If the 2nd stage fan blades were new at their last 
installation onto the 2nd stage fan disk, inspect at the first 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 cycles-since-new (CSN), not to exceed 10,000 CSN.
    (3) Thereafter, inspect the 2nd stage fan blades at each 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 CIS, not to exceed 10,000 CIS since the last 
inspection.
    (4) Guidance on performing ECIs and UIs of the 2nd stage fan 
blade pin-root holes and blade root attachments can be found in 
Pratt & Whitney Maintenance Advisory Notice MAN-JT8D-1-08.
    (5) Remove from service before further flight any 2nd stage fan 
blades that are found cracked.

Optional Terminating Action

    (g) For JT8D-9, -9A, -11, -15, and -17 engines, as optional 
terminating action to the repetitive inspections required by this 
AD, replace the affected 2nd stage fan blades with redesigned 2nd 
stage fan blades using Pratt & Whitney Service Bulletin No. 5866, 
Revision 2, dated October 20, 1998.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, FAA, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Related Information

    (i) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.
    (j) Contact Pratt & Whitney, 400 Main St., East Hartford, CT 
06108; telephone (860) 565-8770; fax (860) 565-4503, for a copy of 
the service information referenced in this AD.

    Issued in Burlington, Massachusetts, on August 3, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E9-18941 Filed 8-6-09; 8:45 am]

BILLING CODE 4910-13-P