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

[Federal Register Volume 74, Number 227 (Friday, November 27, 2009)]
[Rules and Regulations]
[Pages 62229-62231]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-27518]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0317; Directorate Identifier 79-ANE-18; Amendment 
39-16087; AD 2009-24-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding 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 AD replaces the required FPI with eddy current 
inspection (ECI) on all affected 2nd stage fan blades and maintains the 
requirement of UI of the blade root attachment on some of the affected 
2nd stage fan blades. This AD also introduces an optional terminating 
action to the repetitive blade inspections for certain engine models. 
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.

DATES: This AD becomes effective January 4, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 4, 2010.

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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: 
[email protected]; telephone (781) 238-7117, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 87-14-01 R1, Amendment 39-6359 (54 FR 43954, October 30, 
1989), with a proposed AD. The proposed AD applies to JT8D-7, -7A, -7B, 
-9, -9A, -11, -15, and -17 turbofan engines with 2nd stage fan blades, 
P/N 433802, 645902, 759902, 695932, 678102, or 746402 installed. We 
published the proposed AD in the Federal Register on August 7, 2009 (74 
FR 39582). That action proposed to replace the required FPI with ECI on 
all affected 2nd stage fan blades and would maintain the requirement of 
UI of the blade root attachment on some of the affected 2nd stage fan 
blades. That action also proposed to introduce an optional terminating 
action to the repetitive blade inspections for certain engine models.

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 AD, the regulatory

[[Page 62230]]

evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
provided in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.
    One commenter, FedEx Express, requests that we add a requirement to 
the AD to mandate the inspections to be performed at a repair agency 
having engine overhaul capabilities.
    We do not agree. Code of Federal Regulations, 14 Part 43 
(Maintenance, Preventative Maintenance, Rebuilding, and Alteration) 
establish the requirements as to who can perform these types of actions 
on type-certificated products, including the actions specified in this 
AD. Restating these requirements in the AD is unnecessary. We did not 
change the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 1,380 engines installed on 
airplanes of U.S. registry. We also estimate that it will 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 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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
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, 
Amendment 39-16087, to read as follows:

2009-24-01 Pratt & Whitney: Amendment 39-16087. Docket No. FAA-2009-
0317; Directorate Identifier 79-ANE-18.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
4, 2010.

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. Contact 
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503, for a copy of this service 
information.
    (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.

[[Page 62231]]

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: 
[email protected]; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.

Material Incorporated by Reference

    (j) You must use Pratt & Whitney Service Bulletin No. 5866, 
Revision 2, dated October 20, 1998, to perform the optional 
terminating action in this AD. The Director of the Federal Register 
approved the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & 
Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-
8770; fax (860) 565-4503, for a copy of this service information. 
You may review copies at the FAA, New England Region, 12 New England 
Executive Park, Burlington, MA; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 9, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-27518 Filed 11-25-09; 8:45 am]
BILLING CODE 4910-13-P

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