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[Federal Register Volume 76, Number 19 (Friday, January 28, 2011)]
[Rules and Regulations]
[Pages 5066-5068]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1869]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0593; Directorate Identifier 98-ANE-48-AD; 
Amendment 39-16584; AD 2011-03-01]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, 
-15, -15A, -17, -17A, -17R, and -17AR series turbofan engines. That AD 
currently requires revisions to the engine manufacturer's time limits 
section (TLS) to include enhanced inspection of selected critical life-
limited parts at each piece-part opportunity. This AD modifies the TLS 
of the manufacturer's engine manual and an air carrier's approved 
continuous airworthiness maintenance program to incorporate additional 
inspection requirements and reduce the model applicability. This AD was 
prompted by PW developing, and the FAA approving, improved inspection 
procedures for the critical life-limited parts. 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. We are issuing this AD to prevent critical life-
limited rotating engine part failure, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: This AD is effective March 4, 2011.

ADDRESSES: 

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

[[Page 5067]]

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone (781) 238-7178, fax 
(781) 238-7199; e-mail: ian.dargin@faa.gov.

SUPPLEMENTARY INFORMATION: We issued a notice of proposed rulemaking 
(NPRM) to amend 14 CFR part 39 to supersede AD 2005-25-05, Amendment 
39-14398 (70 FR 73361, December 12, 2005). That AD applies to the 
specified products. The NPRM published in the Federal Register on 
August 18, 2010 (75 FR 50942). That NPRM proposed to modify the TLS of 
the manufacturer's engine manual and an air carrier's approved 
continuous airworthiness maintenance program to incorporate additional 
inspection requirements and reduce the model applicability. PW has 
developed and the FAA has approved improved inspection procedures for 
the critical life-limited parts. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data 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 1,527 JT8D -7, -7A, -7B, -9, -
9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines 
installed on airplanes of U.S. registry. We also estimate that it will 
take about 10 work-hours per engine to perform the actions, and that 
the average labor rate is $85 per work-hour. Since this is an added 
inspection requirement, included as part of the normal maintenance 
cycle, no additional part costs are involved. Based on these figures, 
we estimate the total cost of the AD to U.S. operators to be 
$1,297,950.

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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 39-14398 (70 FR 
73361, December 12, 2005), and by adding a new airworthiness directive, 
Amendment 39-16584, to read as follows:

2011-03-01 Pratt & Whitney: Amendment 39-16584. Docket No. FAA-2010-
0593; Directorate Identifier 98-ANE-48-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective March 4, 
2011.

Affected ADs

    (b) This AD supersedes AD 2005-25-05, Amendment 39-14398.

Applicability

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

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of PW JT8D series turbofan 
engines. We are issuing this AD to prevent critical life-limited 
rotating engine part failure, which could result in an uncontained 
engine failure and 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.
    (f) Within the next 30 days after the effective date of this AD, 
(1) revise the Time Limits Section (TLS) of the manufacturer's 
engine manual, part number 481672, as appropriate for PW JT8D-7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series 
turbofan engines, and (2) for air carriers, revise the approved 
mandatory inspections section of the 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.

[[Page 5068]]

------------------------------------------------------------------------
          Description                Section          Inspection No.
------------------------------------------------------------------------
Hub (Disk), 1st Stage
 Compressor:
    * Hub Detail--All P/Ns.....        72-33-31       -03, -04, -05, -06
    * Hub Assembly--All P/Ns...        72-33-31       -03, -04, -05, -06
2nd Stage Compressor:
    Disk--All P/Ns.............        72-33-33                 -02, -03
    Disk Assembly--All P/Ns....        72-33-33                 -02, -03
Disk, 13th Stage Compressor--          72-36-47                      -02
 All P/Ns......................
HP Turbine Disk, First Stage w/        72-52-04                      -03
 integral Shaft--All P/Ns......
HP Turbine, First Stage, w/
 separable Shaft:
    Rotor Assembly--All P/Ns...        72-52-02                      -04
    Disk--All P/Ns.............        72-52-02                      -03
Disk, 2nd Stage Turbine--All P/        72-53-16                      -02
 Ns............................
* Disk, 3rd Stage Turbine--All         72-53-17                 -02, -03
 P/Ns..........................
* Disk (Separable), 4th Stage          72-53-15                 -02, -03
 Turbine--All P/Ns.............
Disk (Integral Disk/Hub), 4th          72-53-18                    -02''
 Stage Turbine--All P/Ns.......
------------------------------------------------------------------------

    (g) The parts that have an Engine Manual Inspection Task and or 
Sub Task Number reference updated in the table of this AD are 
identified by an asterisk (*) that precedes the part nomenclature.
    (h) Except as provided in paragraph (i) of this AD and, 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
shall be performed only in accordance with the TLS of the 
manufacturer's engine manual.

Alternative Methods of Compliance (AMOC)

    (i) You must perform these mandatory inspections using the TLS 
of the manufacturer's engine manual unless you receive approval to 
use an AMOC under paragraph (j) of this AD. Section 43.16 of the 
Federal Aviation Regulations (14 CFR 43.16) may not be used to 
approve alternative methods of compliance or adjustments to the 
times in which these inspections must be performed.
    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Maintaining Records of the Mandatory Inspections

    (k) You have met the requirements of this AD when you revise the 
TLS of the manufacturer's engine manual as specified in paragraph 
(f) of this AD. For air carriers operating under part 121 of the 
Federal Aviation Regulations (14 CFR part 121), you have met the 
requirements of this AD when you modify your continuous 
airworthiness maintenance plan to reflect those changes. You do not 
need to record each piece-part inspection as compliance to this AD, 
but you must maintain records of those inspections according to the 
regulations governing your operation. For air carriers operating 
under part 121, you may use either the system established to comply 
with section 121.369 or an alternative accepted by your principal 
maintenance inspector if that alternative:
    (1) Includes a method for preserving and retrieving the records 
of the inspections resulting from this AD; and
    (2) Meets the requirements of section 121.369(c); and
    (3) Maintains the records either indefinitely or until the work 
is repeated.
    (l) These record keeping requirements apply only to the records 
used to document the mandatory inspections required as a result of 
revising the TLS of the manufacturer's engine manual as specified in 
paragraph (f) of this AD. These record keeping requirements do not 
alter or amend the record keeping requirements for any other AD or 
regulatory requirement.

Related Information

    (m) For more information about this AD, contact Ian Dargin, 
Aerospace Engineer, Engine Certification Office, FAA, Engine and 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone (781) 238-7178, fax (781) 238-7199; e-mail: 
ian.dargin@faa.gov.

    Issued in Burlington, Massachusetts, on January 24, 2011.
Thomas A. Boudreau,
Acting Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2011-1869 Filed 1-27-11; 8:45 am]
BILLING CODE 4910-13-P
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