[Federal Register Volume 78, Number 209 (Tuesday, October 29, 2013)]
[Proposed Rules]
[Pages 64419-64421]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-25459]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043,
PW2146, PW2240, PW2337, PW2643, and F117-PW-100 turbofan engines. This
proposed AD was prompted by a rupture of the diffuser-to-high-pressure
turbine (HPT) case flange. This proposed AD would require a one-time
eddy current inspection (ECI) of affected engines with certain diffuser
and HPT cases installed. This AD also proposes to require a
fluorescent-penetrant inspection (FPI) of the diffuser case rear flange
and HPT case front flange. We are proposing this AD to prevent failure
of the diffuser-to-HPT case flange, which could lead to uncontained
engine failure and damage to the airplane.
DATES: We must receive comments on this proposed AD by December 30,
2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-565-
8770; fax: 860-565-4503. You may view this service information at the
FAA, Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA. For information on the availability of this material at
the FAA, call 781-238-7125.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7154;
fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2013-0740;
Directorate Identifier 2013-NE-24-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because 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 we
receive about this proposed AD.
Discussion
We received a report of an engine event in October 2011 that
resulted in a rupture of the engine diffuser-to-HPT case flange. The
rupture caused the engine cowl doors to break open, which resulted in
damage to the underside of the airplane's wing. Subsequent
investigation revealed that the root cause of this rupture was a crack
that originated in HPT case M-flange boltholes (the forward flange of
the HPT case that mates with the rear outer flange of the diffuser
case). This condition, if not corrected, could result in failure of the
diffuser-to-HPT case flange, which may cause an uncontained engine
failure and damage to the airplane.
[[Page 64420]]
Relevant Service Information
We reviewed PW Service Bulletin (SB) No. PW2000 72-763, Revision 1,
dated August 30, 2013, and PW PW2000 Series Engine Manual part number
1A6231. The SB describes procedures for inspecting the flanges of the
HPT case and the diffuser case.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require an on-wing ECI of the diffuser case
and HPT case flanges. This proposed AD would also require an FPI of all
engine diffuser cases and all HPT cases.
Differences Between the Proposed AD and the Service Information
PW SB No. PW2000 72-763, Revision 1, dated August 30, 2013,
requires that operators complete an on-wing ECI by August 31, 2013. We
are proposing that the ECI be performed within 100 flight cycles or 30
days after the effective date of this AD, whichever is earlier.
Costs of Compliance
We estimate that this proposed AD will affect 638 engines installed
on airplanes of U.S. registry. Of the 638 engines, we estimate that
about 58 engines will be subject to ECI and all engines will be subject
to the FPI. We also estimate that it would take about 5 hours to
perform the ECI and 3 hours to perform the FPI required by this
proposed AD. Materials cost for the FPI will be about $20 per engine.
The average labor rate is $85 per hour. Based on these figures, we
estimate the total cost of this proposed AD to U.S. operators to be
$200,100.
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 proposed 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 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 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),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, 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, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 adding the following new airworthiness
directive (AD):
Pratt & Whitney: Docket No. FAA-2013-0740; Directorate Identifier
2013-NE-24-AD.
(a) Comments Due Date
We must receive comments by December 30, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D,
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643,
and F117-PW-100 turbofan engines.
(d) Unsafe Condition
This AD was prompted by a rupture of the diffuser-to-high-
pressure turbine (HPT) case flange. We are issuing this AD to
prevent failure of the diffuser-to-HPT case flange, which could lead
to uncontained engine failure and damage to the airplane.
(e) Compliance
Unless already done, comply with this AD within the compliance
times specified.
(1) For diffuser and HPT cases identified by serial number (S/N)
in Table 1 to paragraph (e) of this AD:
(i) Within 100 flight cycles or 30 days after the effective date
of this AD, whichever is earlier, eddy current inspect the diffuser
case and the HPT case M-flange.
(ii) For engines installed on the aircraft, use paragraphs 3.G.
through 3.L. in the ``For Engines Installed on the Aircraft''
section of the Accomplishment Instructions of PW Service Bulletin
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to
perform the inspection.
(iii) For engines removed from the aircraft, use paragraphs 3.B.
through 3.G. in the ``For Engines Removed From the Aircraft''
section of the Accomplishment Instructions of PW Service Bulletin
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to
perform the inspection.
Table 1 to Paragraph (e)--Diffuser and HPT Case P/Ns and Serial Numbers
----------------------------------------------------------------------------------------------------------------
Diffuser case part No. (P/N) Diffuser case S/N HPT case P/N HPT case S/N
----------------------------------------------------------------------------------------------------------------
1B7407-001........................... DGUSAA0114............. 1A9030................. RM6300
1B7407............................... WE2452................. 1B2440................. DKLBB40125
1B7407............................... DGUSAA0097............. 1B2440................. DKLBCH3429
1B7407............................... DGUSAA0670............. 1B2440................. DKLBCS1032
1B7407-001........................... DGUSAA0622............. 1B2440................. DKLBC00030
1B3055-001........................... DGUSAA0247............. 1B2440................. DKLBC07691
1B7461............................... DGGUAK1308............. 1B2440................. DKLBDB5108
[[Page 64421]]
1B7461............................... DGGUAK1306............. 1B2440................. DKLBDB5153
1B7461............................... DGGUAK1356............. 1B2440................. DKLBDU3358
1B7477............................... DGGUAL1445............. 1A9030................. RM6353
1B7477............................... DGGUAL1492............. 1A9030................. PD3348
1B7477............................... DGGUAL1501............. 1A9030................. PD3280
1B7477............................... DGGUAL1597............. 1A9030................. ND5644
1B4091-001........................... RT6356................. 1B2440................. DKLBBP0225
1B4091-002........................... ST2044................. 1A9030................. DKLBBR3621
1B4091-005........................... PF3203................. 1A9030................. PD3290
1B7461............................... DGGUAK1377............. 1B2440................. WG6904
1B7477............................... DGGUAL1548............. 1B2440................. WV1807
1B7407............................... DGGUAK0189............. 1B2440................. WX2639
1B7407............................... DGUSAA0443............. 1B2440................. WZ4057
1B7477............................... DGGUAL1441............. 1B2440................. WX2664
1B7477............................... DGGUAL1560............. 1A9030................. RM6359
1B7407-001........................... DGUSAA0329............. 1B2440................. DKLBCM8956
1B7407............................... DGUSAA0334............. 1B2440................. DKLBCM0214
1B2440................. DKLBDB5069
1B2440................. DKLBB02548
1B2440................. DKLBDC7336
1B2440................. DKLBDU3372
1B2440................. WM6913
1B2440................. DKLBBF6606
1B2440................. DKLBBB2861
1B2440................. DKLBCT1660
1B2440................. DKLBB94641
1B2440................. DKLBBX8092
----------------------------------------------------------------------------------------------------------------
(2) For all diffuser and HPT cases:
(i) At the next piece part exposure and every piece part
exposure thereafter, perform a high sensitivity fluorescent-
penetrant inspection (FPI) of the entire diffuser case rear flange
(M-flange) and bolt holes.
(ii) At the next piece part exposure and every piece part
exposure thereafter, perform a high sensitivity FPI of the entire
HPT case forward flange (M-flange) and bolt holes.
(f) Prohibition Statement
After the effective date of this AD, do not install any engine
with a diffuser or HPT case with serial number listed in Table 1 to
paragraph (e) of this AD, onto any aircraft, that was not inspected
per paragraph (e) of this AD.
(g) Credit for Previous Actions
If you performed an eddy current inspection of the diffuser case
and HPT case M-flange using paragraphs 3.G. through 3.L. in the
``For Engines Installed on the Aircraft'' section or paragraphs 3.B.
through 3.G. in the ``For Engines Removed from the Aircraft''
section of the Accomplishment Instructions of PW SB PW2000 72-763,
dated March 22, 2013, you met the requirements of paragraph (e)(1)
of this AD.
(h) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(i) Related Information
(1) For more information about this AD, contact Robert Morlath,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7154; fax: 781-238-7199; email:
[email protected].
(2) Pratt & Whitney Engine Manual, part number 1A6231, Chapter
72-41-00, Inspection/Check-02, (Task 72-41-00-230-002) and Chapter
72-52-00, Inspection/Check-02 (Task 72-52-00-230-000), which are not
incorporated by reference in this AD, can be obtained from Pratt &
Whitney, using the contact information in paragraph (i)(3) of this
AD.
(3) For service information identified in this AD, contact Pratt
& Whitney, United Technologies Corporation, 400 Main St., East
Hartford, CT 06108; phone: 860-565-8770; fax: 860-565-4503.
(4) You may view this service information at the FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call 781-238-7125.
Issued in Burlington, Massachusetts, on October 7, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2013-25459 Filed 10-28-13; 8:45 am]
BILLING CODE 4910-13-P