[Federal Register: June 30, 2003 (Volume 68, Number 125)]
[Rules and Regulations]
[Page 38592-38594]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jn03-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-24-AD; Amendment 39-13211; AD 2003-13-11]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW4074, PW4074D,
PW4077, PW4077D, PW4090, and PW4090-3 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Pratt & Whitney (PW) PW4074, PW4074D, PW4077, PW4077D, PW4090, and
PW4090-3 turbofan engines with high pressure compressor (HPC) rear
cases, part numbers (P/Ns) 55H425-01, 55H385-01, and 56H396-01
installed. This AD requires initial and repetitive visual or
fluorescent penetrant inspections (FPI) of the J flange on the HPC rear
case, and removal from service of the rear case based on certain
inspection results. This AD is prompted by reports of cracks
propagating from bolt holes in the HPC rear case J flange, and reports
of high-cycle HPC rear cases exhibiting cracks propagating into the
shell wall. The actions specified in this AD are intended to prevent
fracturing and rupturing of the HPC rear case, resulting in uncontained
engine failure.
DATES: Effective July 15, 2003. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of July 15, 2003.
We must receive any comments on this AD by August 29, 2003.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
[sbull] By mail: The Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2003-NE-24-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055.
[sbull] By e-mail: 9-ane-adcomment@faa.gov
You may get the service information referenced in this AD from
Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860)
565-6600; fax (860) 565-4503.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information at the FAA, New
England Region, Office of the Regional 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.
FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7189; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: This AD applies to PW PW4074, PW4074D,
PW4077, PW4077D, PW4090, and PW4090-3 turbofan engines with HPC rear
cases, P/Ns 55H425-01, 55H385-01, and 56H396-01 installed. This AD
requires initial and repetitive visual or FPI inspections of the J
flange on HPC rear cases, P/Ns 55H425-01, 55H385-01, and 56H396-01,
which were previously produced with or modified to a scalloped flange
configuration using PW Service Bulletin (SB) No. PW4G-112-72-150, dated
April 16, 1998, or SB No. PW4G-112-72-151, dated April 16, 1998, or SB
No. PW4G-112-72-195, dated May 5, 1999. This AD also requires removal
from service of the rear case based on certain inspection results. This
AD is prompted by 32 reports of cracks propagating from bolt holes in
the HPC rear case J flange, and reports of high-cycle HPC rear cases
exhibiting cracks propagating into the shell wall. The HPC rear cases,
P/Ns 55H425-01, 55H385-01, and 56H396-01 were produced with or modified
by PW SBs to incorporate a scalloped J flange design as corrective
action to eliminate flange cracking at the bolt holes. The scalloped
flange has not been effective in eliminating J flange cracking. Cracks
found propagating into the shell wall could result in loss of case
integrity, and require immediate removal before further flight. The
actions specified in this AD are intended to prevent fracturing and
rupturing of the HPC rear case, resulting in uncontained engine
failure.
Relevant Service Information
We have reviewed and approved the technical contents of PW SB No.
PW4G-112-72-256, dated April 2, 2003, that describes procedures for
initial and repetitive visual or FPI inspections of the J flange on HPC
rear cases, and removal from service of the rear case based on certain
inspection results.
[[Page 38593]]
Differences Between This AD and the Service Information
This AD adds an additional inspection at bolt hole location number
69, which was not originally listed in PW SB No. PW4G-112-72-256,
because one report of a crack at that location has been received since
the service bulletin was released. Future revisions of PW SB No. PW4G-
112-72-256 will include this inspection location.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other PW PW4074, PW4074D, PW4077, PW4077D, PW4090, and
PW4090-3 turbofan engines of the same type design. Therefore, we are
issuing this AD to prevent fracturing and rupturing of the HPC rear
case, resulting in uncontained engine failure. This AD requires:
[sbull] Initial and repetitive visual or FPI inspections of the J
flange on HPC rear cases, P/Ns 55H425-01, 55H385-01, and 56H396-01.
[sbull] Removal of the rear case from service based on certain
inspection results.
You must do these actions in accordance with the service
information described previously.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
prior public comment are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Changes to 14 CFR Part 39--Effect on the AD
On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs our AD system. This regulation now
includes material that relates to special flight permits, alternative
methods of compliance, and altered products. This material previously
was included in each individual AD. Since this material is included in
14 CFR part 39, we will not include it in future AD actions.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-24-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the rule
that might suggest a need to modify it. If a person contacts us through
a nonwritten communication, and that contact relates to a substantive
part of this AD, we will summarize the contact and place the summary in
the docket. We will consider all comments received by the closing date
and may amend the AD in light of those comments.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You may get more information about plain
language at http://www.plainlanguage.gov.
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 the 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); 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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-NE-24-AD'' in your request.
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 part 39 of the Federal
Aviation Regulations (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:
2003-13-11 Pratt & Whitney: Amendment 39-13211. Docket No. 2003-NE-
24-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 15,
2003.
Affected ADs
(b) None.
Applicability
(c) This AD is applicable to Pratt & Whitney (PW) PW4074,
PW4074D, PW4077, PW4077D, PW4090, and PW4090-3 turbofan engines with
high pressure compressor (HPC) rear cases, part numbers (P/Ns)
55H425-01, 55H385-01, and 56H396-01 installed. These engines are
installed on, but not limited to, Boeing 777 series airplanes.
Unsafe Condition
(d) This AD is prompted by 32 reports of cracks propagating from
bolt holes in the HPC rear case J flange, two of which were reports
of high-cycle HPC rear cases with cracks propagating into the shell
wall, which required immediate removal before further flight. The
actions specified in this AD are intended to prevent fracturing and
rupturing of the HPC rear case, resulting in uncontained engine
failure.
Compliance
(e) Compliance with this AD is required as indicated, unless
already done.
Initial Inspection
(f) Perform an initial visual or fluorescent penetrant
inspection (FPI) of the HPC rear case J flange for cracks at bolt
hole location numbers 22, 67, 68, and 69, in accordance with
Accomplishment Instructions of PW Service Bulletin (SB) No. PW4G-
112-72-256, dated April 2, 2003, using the compliance times
specified in the following Table 1:
[[Page 38594]]
Table 1.--Initial Inspection Schedule
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For cycles
HPC rear case P/N accumulated of: Then:
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(1) 55H425-01 modified by PW SB (i) 4,000 or more Inspect within 50
No. PW4G-112-72-150, dated cycles-since SB cycles-in-service
April 16, 1998. modification (CIS) after the
(CSM). effective date of
this AD.
(ii) 2,500 CSM or Inspect within 75
more, but fewer CIS after the
than 4,000 CSM. effective date of
this AD.
(iii) 1,850 CSM or Inspect within 150
more, but fewer CIS after the
than 2,500 CSM. effective date of
this AD.
(iv) More than Inspect within 300
1,700 CSM, but CIS after the
fewer than 1,850 effective date of
CSM. this AD.
(v) 1,700 CSM, or Inspect before
fewer. accumulating
2,000 CSM
---------------------------------
(2) 55H385-01, 55H396-01, and (i) 7,200 or more Inspect within 300
55H425-01 incorporating a CSN. CIS after the
scalloped J. effective date of
this AD.
(ii) Fewer than Inspect before
7,200 CSN. accumulating
7,500 CSN.
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Previous Credit
(g) Previous credit is allowed for initial inspections for
cracks at bolt hole location numbers 22, 67, and 68 that were done
in accordance with PW SB PW4G-112-72-256, dated April 2, 2003,
before the effective date of this AD. Previous credit is also
allowed for initial inspection of bolt hole location number 69 if
bolt hole location number 68 was previously inspected before the
effective date of this AD.
(h) Disposition the HPC rear cases using the criteria in the
following Table 2:
Table 2.--HPC Rear Case Disposition Criteria
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If HPC rear case has: Then:
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(1) One or more inboard cracks that have Remove HPC rear case before
penetrated beyond the pedestal and into further flight.
the shell wall.
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(2) One or more inboard cracks that have Remove HPC rear case within
penetrated into the pedestal but not into 25 cycles-since-last
the shell wall. inspection (CSLI).
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(3) One or more inboard cracks that have Remove HPC rear case within
not penetrated into the pedestal. 250 CSLI.
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(4) One or more outboard cracks........... Perform repetitive
inspections as specified in
paragraph (i) of this AD.
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(5) No cracks............................. Perform repetitive
inspections as specified in
paragraph (i) of this AD.
------------------------------------------------------------------------
Repetitive Inspections
(i) Perform repetitive inspections of the HPC rear case J flange
for cracks at bolt hole location numbers 22, 67, 68, and 69 in
accordance with the Accomplishment Instructions of PW SB No. PW4G-
112-72-256, dated April 2, 2003, and the following:
(1) If last inspection of HPC rear case was a visual inspection,
then visually inspect or FPI within:
(i) 600 CSLI if no cracks are found.
(ii) 300 CSLI if one or more outboard cracks are found.
(2) If last inspection of HPC rear case was an FPI, then
visually inspect or FPI within:
(i) 1,000 CSLI if no cracks are found.
(ii) 600 CSLI if one or more outboard cracks are found.
(3) Remove HPC rear cases from service or re-inspect rear cases
using Table 2 of this AD.
Alternative Methods of Compliance
(j) Alternative methods of compliance must be requested in
accordance with 14 CFR part 39.19, and must be approved by the
Manager, Engine Certification Office, FAA.
Material Incorporated by Reference
(k) The inspections and removal from service of HPC rear cases
must be done in accordance with Pratt & Whitney Service Bulletin No.
PW4G-112-72-256, dated April 2, 2003. 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. You
may get a copy from Pratt & Whitney, 400 Main St., East Hartford, CT
06108, telephone (860) 565-6600; fax (860) 565-4503. You may review
copies at the FAA, New England Region, Office of the Regional
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.
Related Information
(l) None.
Issued in Burlington, Massachusetts, on June 18, 2003.
Robert Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-15992 Filed 6-27-03; 8:45 am]
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