Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines, 77342-77345 [E5-8099]
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77342
Proposed Rules
Federal Register
Vol. 70, No. 250
Friday, December 30, 2005
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE–30-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt &
Whitney JT8D–1, –1A, –1B, –7, –7A,
–7B, –9, –9A, –11, –15, –15A, –17,
–17A, –17R, –17AR, –209, –217, –217A,
–217C, and –219 Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Pratt & Whitney (PW)
JT8D–209, –217, –217A, –217C, and
–219 turbofan engines. That AD
currently requires initial and repetitive
visual inspections for fretting and
fluorescent magnetic particle
inspections (FMPI) for cracking in the
area of the tierod holes on 8th stage high
pressure compressor (HPC) front hubs
(from here on, referred to as HPC front
hubs) that have operated at any time
with PWA 110–21 coating. This
proposed AD would require either
replacing HPC front hubs and HPC disks
that have operated at any time with
PWA 110–21 coating and that operated
in certain engine models, or, visually
inspecting and FMPI for cracking of
those parts and replating them if they
pass inspection. This proposed AD
would also require adding JT8D–1, –1A,
–1B, –7, –7A, –7B, –9, –9A, –11, –15,
–15A, –17, 17A, 17R, and 17AR
engines to the applicability. This
proposed AD results from an
investigation by PW, which concluded
that any HPC front hub or HPC disk
coated with PWA 110–21 that ever
operated on JT8D–15, –15A, –17, –17A,
–17R, –17AR, –209, –217, –217A,
–217C, and –219 turbofan engines,
could crack before reaching their
published life limit. We are proposing
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this AD to prevent a rupture of an HPC
front hub or an HPC disk that could
result in an uncontained engine failure
and damage to the airplane.
DATES: We must receive any comments
on this proposed AD by February 28,
2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001 NE–
30–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
Contact Pratt & Whitney, 400 Main
St., East Hartford, CT 06108, telephone
(860) 565–7700; fax (860) 565–1605 for
the service information identified in this
proposed AD.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
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:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
2001–NE–30–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 datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed 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
proposed AD in light of those
comments.
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Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and any final disposition by
appointment, between 8 a.m. and 4:30
p.m., Monday through Friday, except
Federal holidays. See ADDRESSES for the
location.
Discussion
On November 15, 2002, we issued AD
2002–23–14, Amendment 39–12958 (67
FR 70686, November 26, 2002). That AD
requires initial and repetitive visual
inspections for fretting and FMPI for
cracking in the area of the tierod holes
on HPC front hubs that have operated at
any time with PWA 110–21 coating.
That AD resulted from the discovery of
cracking in the area of the tierod holes,
found during routine engine overhauls.
That condition, if not corrected, could
result in an uncontained engine failure
and damage to the airplane.
Actions After We Issued AD 2002–23–
14
After we issued AD 2002–23–14, PW
completed their investigation to
determine the cause of cracking in the
area of the tierod holes on HPC front
hubs. As part of that investigation, PW
looked at seven HPC front hubs coated
with PWA 110–21. They found fretting,
cracks, or both, at the rear bolt face of
the HPC front hub on six of the seven
HPC front hubs. This was similar to the
cracks seen in PW’s initial investigation
into this issue. Most of the seven hubs
had low cycle time, with the lowest
being 2,800 cycles-since-new.
Additional cracks were found on other
stages of HPC disks, both with nickelcadmium, and PWA 110–21 coating. PW
determined that all HPC front hubs and
HPC disks that have ever been coated
with PWA 110–21 and that have ever
been operated on JT8D–15, –15A, –17,
–17A, –17R, –17AR, –209, –217, –217A,
–217C, and –219 turbofan engines, have
a higher risk of fracturing before
reaching their published life limit of
20,000 cycles-in-service, than HPC front
hubs and HPC disks plated with nickelcadmium.
Relevant Service Information
We have reviewed and approved the
technical contents of PW Alert Service
Bulletin (ASB) No. JT8D A6430,
Revision 2, dated December 23, 2004,
applicable to JT8D–209, –217, –217A,
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Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Proposed Rules
–217C, and –219 turbofan engines, and
PW ASB No. JT8D A6468, dated
December 23, 2004, applicable to JT8D–
1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11,
–15, –15A, –17, –17A, –17R, and –17AR
turbofan engines. Those ASBs describe
procedures for visual inspections for
fretting wear and FMPI for cracking of
HPC front hubs that have operated with
PWA 110–21 coating in the interface
between the HPC front hub and the
stage 8–9 spacer. Those ASBs also
describe procedures for replating HPC
front hubs using nickel-cadmium, and
replating stage 8–9 spacers using nickelcadmium or electroless nickel.
Differences Between the Proposed AD
and the Manufacturer’s Service
Information
Although the ASBs only require
inspection of the HPC front hubs and
stage 8–9 spacers, we propose to require
inspecting all 7th stage HPC disks and
9th stage-through-12th stage HPC disks
for fretting wear and FMPI for cracking
at the same time the HPC front hub is
visually inspected. These other HPC
disks, which are coated with PWA 110–
21, have increased risk of cracking and
failure.
FAA’s Determination and Requirements
of the Proposed AD
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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. We are proposing this AD,
which would require:
• Visual inspections for fretting wear
and FMPI of HPC front hubs, HPC disks,
and stage 8–9 spacers that at any time
operated coated with PWA 110–21,
replacing them if necessary; replating
those HPC front hubs and disks using
nickel-cadmium, and replating stage 8–
9 spacers using nickel-cadmium or
electroless nickel;
OR
• As optional terminating action to
the visual inspections in the proposed
AD, replacing HPC front hubs, HPC
disks, and stage 8–9 spacers that at any
time operated coated with PWA 110–21
in JT8D–15, –15A, –17, –17A, –17R,
–17AR, –209, –217, –217A, –217C, or
–219 turbofan engines.
• Replacement must be with HPC
front hubs and HPC disks plated with
nickel-cadmium that have never
operated with PWA 110–21 coating, and
stage 8–9 spacers plated with nickelcadmium or electroless nickel.
The proposed AD would require that
you do these actions using the service
information described previously.
Costs of Compliance
About 1,573 JT8D–1, –1A, –1B, –7,
–7A, –7B, –9, –9A, –11, –15, –15A, –17,
–17A, –17R, and –17AR turbofan
engines, and 1,280 JT8D–200 series
turbofan engines, installed on airplanes
of U.S. registry would be affected by this
proposed AD. We estimate it would take
about 12 work hours per engine to
perform the proposed actions, and the
average labor rate is $65 per work hour.
We also estimate 175 of those engines
would be removed before reaching
scheduled maintenance, and would
require an additional 60 work hours to
disassemble and reassemble each
engine. Based on these figures, we
estimate the total cost of the proposed
AD to U.S. operators to be $2,907,840.
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 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 110–2134, 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 summary of the costs
to comply with this proposal 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.
2001–NE–30–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–12958 (67 FR
70686, November 26, 2002) and by
adding a new airworthiness directive to
read as follows:
Pratt & Whitney: Docket No. 2001–NE–30–
AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
February 28, 2006.
Affected ADs
(b) This AD supersedes AD 2002–23–14,
Amendment 39–12958.
Applicability
(c) This AD applies to all Pratt & Whitney
(PW) JT8D–1, –1A, –1B, –7, –7A, –7B, –9,
–9A, –11, –15, –15A, –17, –17A, –17R,
–17AR, –209, –217, –217A, –217C, and –219
turbofan engines, with 8th stage high
pressure compressor (HPC) front hubs (from
here on, referred to as HPC front hubs) as
defined in the following Table 1:
TABLE 1.—AD APPLICABILITY
If:
And the HPC front hub:
Then this AD is:
(1) The HPC front hub at any time operated coated
with PWA 110–21.
Operated in a JT8D–15, –15A, –17, –17R, –17AR,
–209, –217, –217A, –217C, or –219 engine.
Applicable.
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77344
Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Proposed Rules
TABLE 1.—AD APPLICABILITY—Continued
If:
And the HPC front hub:
Then this AD is:
(2) The HPC front hub at any time had coating in the
interface between the HPC front hub and the stage
8–9 spacer (PWA 110–21 coating applied to spacer).
(3) The HPC front hub and HPC disks have PWA
110–21 coating.
Operated in a JT8D–209, –217, –217A, –217C, or
–219 engine.
Applicable.
Operated in a JT8D–1, –1A, –1B, –7, –7A, –7B, –9,
–9A, or –11 engine, but never operated in a JT8D–
15, –15A, –17, –17A, –17R, –17AR, –209, –217,
–217A, –217C, or –219 engine.
......................................................................................
Not applicable.
(4) The HPC front hub has never operated with PWA
110–21 coating in the interface with the stage 8–9
spacer, either on the HPC front hub or on the stage
8–9 spacer.
These engines are installed on, but not
limited to, Boeing DC–9, MD–80 series, 727
series, and 737 series airplanes.
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.
Unsafe Condition
(d) This AD results from an investigation
by PW, which concluded that any HPC front
hub or HPC disk coated with PWA 110–21
that ever operated on JT8D–15, –15A, –17,
–17A, –17R, –17AR, –209, –217, –217A,
–217C, and –219 turbofan engines, could
crack before reaching their published life
limit. We are issuing this AD to prevent a
rupture of an HPC front hub or an HPC disk
that could result in an uncontained engine
failure and damage to the airplane.
JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11,
–15, –15A, –17, –17A, –17R, and –17AR
Turbofan Engines—Inspect or Replace HPC
Front Hubs, HPC Disks, and Stage 8–9
Spacers
(f) For JT8D–1, –1A, –1B, –7, –7A, –7B, –9,
–9A, –11, –15, –15A, –17, –17A, –17R, and
–17AR turbofan engines, do the following:
Not applicable.
(1) Using the inspection schedule in Table
2 of this AD, strip the protective coating,
visually inspect for fretting wear, fluorescent
magnetic particle inspect (FMPI) for cracks,
reidentify, replate HPC front hubs and stage
8–9 spacers, and replace if necessary.
(2) Use paragraphs 1 through 3.B.(7)(b)
under ‘‘For Rear Compressor Front Hubs that
Have Operated With PWA 110–21 coating AT
ANY TIME During Their Service Life in
JT8D–15, –15A, –17, –17A, –17R, –17AR
Engine Models.’’ of PW Alert Service Bulletin
(ASB) JT8D A6468, dated December 23, 2004.
TABLE 2.—HPC DISK INSPECTION SCHEDULE
HPC front hub cycles-since-new (CSN) on the
effective date of this AD
Inspect before additional cycles-in-service
(CIS) or CSN, whichever occurs first
Also inspect 7th stage HPC disks and 9th
stage-through-12th stage HPC disks using:
(i) 19,000 or more
(ii) 15,500 or more, but fewer than 19,000.
(iii) Fewer than 15,500.
(iv) Fewer than 5,000 that are accessible.
500 CIS or 20,000 CSN
1,000 CIS or 19,500 CSN.
5,000 CIS or 16,500 CSN.
...........................................................................
Paragraph (f)(3) of this AD
Paragraph (f)(3) of this AD.
Paragraph (f)(3) of this AD.
Paragraph (f)(3) of this AD. If the parts pass
inspection, parts may be reinstalled. Inspect
again using the criteria listed in (iii) of this
Table.
(3) When the HPC front hub is inspected,
visually inspect for fretting wear and FMPI
for cracks on 7th stage HPC disks and 9th
stage-through-12th stage HPC disks.
Inspection information can be found in the
applicable sections of JT8D Engine Manual
Part Number (P/N) 481672, listed in the
following Table 3:
TABLE 3.—7TH STAGE HPC DISKS AND 9TH STAGE-THROUGH-12TH STAGE HPC DISKS INSPECTION INFORMATION
Chapter/
Section
7 ......
9 ......
10 ....
11 ....
12 ....
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Stage
72–36–41
72–36–43
72–36–44
72–36–45
72–36–46
Visual inspection
Inspection–01
Inspection–01
Inspection–01
Inspection–01
Inspection–01
.......................................
.......................................
.......................................
.......................................
.......................................
JT8D–15, –15A, –17, –17A, –7R, and –17AR
Turbofan Engines—Cycle Adjustment for
HPC Front Hubs That Entered Service With
Nickel-Cadmium Plating and PWA 110–21
Coating
(g) For JT8D–15, –15A, –17, –17A, –17R,
and –17AR turbofan engines with front hubs
that entered service with nickel-cadmium
plating and PWA 110–21 coating, but have
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Fretting inspection
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Inspection–04
Inspection–04
Inspection–04
Inspection–04
Inspection–04
.......................................
.......................................
.......................................
.......................................
.......................................
also operated during the life of the hub with
PWA 110–21 coating:
(1) You are allowed to make a cycle
adjustment if the hub was never operated
with a PWA 110–21-coated stage 8–9 spacer.
(2) Use the information under
‘‘Compliance’’ of PW ASB JT8D A6468, dated
December 23, 2004, to determine the
adjustment.
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Inspection–03.
Inspection–03.
Inspection–03.
Inspection–03.
Inspection–03.
JT8D–209, –217, –217A, –217C, and –219
Turbofan Engines—Inspect or Replace HPC
Front Hubs and Stage 8–9 Spacers
(h) For JT8D–209, –217, –217A, –217C, and
–219 turbofan engines, do the following:
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Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Proposed Rules
(1) Using the inspection schedule in Table
4 of this AD, strip the protective coating,
visually inspect for fretting wear, FMPI for
cracking, reidentify, replate HPC front hubs
and the stage 8–9 spacers, and replace if
necessary.
(2) Use paragraphs 1. through 1.A. and
paragraphs 2 through 2.C.(2)(g)2 of
77345
Accomplishment Instructions of PW ASB
JT8D A6430, Revision 2, dated December 23,
2004.
TABLE 4.—HPC DISK INSPECTION SCHEDULE
HPC front hub CSN on the effective date of
this AD
Inspect before additional CIS or CSN, whichever occurs first
Also inspect 7th stage HPC disks and 9th
stage-through-12th stage HPC disks using:
(i) 19,000 or more ..............................................
(ii) 15,500 or more, but fewer than 19,000 .......
(iii) Fewer than 15,500 ......................................
(iv) Fewer than 5,000 that are accessible .........
500 CIS or 20,000 CSN ...................................
1,000 CIS or 19,500 CSN ................................
5,000 CIS or 16,500 CSN ................................
......................................................................
Paragraph (h)(3) of this AD.
Paragraph (h)(3) of this AD.
Paragraph (h)(3) of this AD.
Paragraph (h)(3) of this AD. If the parts pass
inspection, parts may be reinstalled. Inspect
again using the criteria listed in (iii) of this
Table.
(3) When the HPC front hub is inspected,
visually inspect for fretting wear and FMPI
for cracks on 7th stage HPC disks and 9th
stage through 12th stage HPC disks.
Inspection information can be found in the
applicable sections of JT8D–200 Engine
Manual P/N 773128, listed in Table 3 of this
AD.
(l) Do not recoat the 7th stage disk with
PWA 110–21 (Repair-15 of Chapter/Section
72–36–41 of JT8D–200 Engine Manual, P/N
773128, and Repair-15 of Chapter/Section
72–36–41 of JT8D Engine Manual, P/N
481672).
(m) Do not recoat the stage 8–9 spacer with
PWA 110–21 (Repair-03, Task 72–36–12–30–
003–002, of Chapter/Section 72–36–12 of
JT8D–200 Engine Manual, P/N 773128, and
Repair-01, Task 72–36–12–30–001–002, of
Chapter/Section 72–36–12 of JT8D Engine
Manual, P/N 481672).
DEPARTMENT OF THE INTERIOR
JT8D–209, –217, –217A, –217C, and –219
Turbofan Engines—Cycle Adjustment for
HPC Front Hubs That Entered Service With
Nickel-Cadmium Plating and PWA 110–21
Coating
(i) For JT8D–209, –217, –217A, –217C, and
–219 turbofan engines with HPC front hubs
that entered service with nickel-cadmium
plating, but have also operated during the life
of the hub with PWA 110–21 coating:
(1) You are allowed to make a cycle
adjustment.
(2) Use the information under
‘‘CONDITION A’’ of PW ASB JT8D A6430,
Revision 2, dated December 23, 2004, to
determine the adjustment.
Replacement of HPC Front Hubs and Stage
8–9 Spacers That Have Operated With PWA
110–21 Coating, As Optional Terminating
Action—All Engines
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(j) For all applicable engines, as optional
terminating action for the repetitive visual
inspections in this AD, replace HPC front
hubs and stage 8–9 spacers that have
operated with PWA 110–21 coating in the
interface between the hub and the stage 8–
9 spacer and HPC disks currently coated with
PWA 110–21, as follows:
(1) Install a nickel-cadmium plated HPC
front hub that has never operated with PWA
110–21 coating in the interface between the
HPC front hub and the stage 8–9 spacer.
(2) Install a nickel-cadmium plated or
electroless nickel-plated stage 8–9 spacer.
(3) Install HPC disks that have never
operated with PWA 110–21 coating.
Prohibition Against Recoating the HPC Front
Hub, Stage 7 HPC Disk, and Stage 8–9
Spacer With PWA 110–21—All Engines
(k) Do not recoat the HPC front hub with
PWA 110–21 (Repair-23 of Chapter/Section
72–36–42 of JT8D–200 Engine Manual, P/N
773128, and Repair-27 and Repair-28 of
Chapter/Section 72–36–42 of JT8D Engine
Manual, P/N 481672).
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Definitions
(n) For the purposes of this AD, a shop
visit is an engine removal, where engine
maintenance entails separating pairs of major
engine flanges or removing a disk, hub, or
spool at a maintenance facility, regardless of
other planned maintenance, except as
follows:
(1) Removing the engine to perform field
maintenance type activities at a maintenance
facility in lieu of performing them on-wing
is not a ‘‘shop visit.’’
(2) Separating flanges of the Combustion
Chamber and Turbine Fan Duct Assembly
(split flanges) to access non-rotating
accessory hardware is not a ‘‘shop visit.’’
(3) Separating flanges to ship the engine
without subsequent internal maintenance is
not a ‘‘shop visit.’’
(o) For the purposes of this AD
accessibility of the HPC front hub is
removing the hub from the engine and
deblading that hub.
Alternative Methods of Compliance
(p) 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.
Related Information
(q) None.
Issued in Burlington, Massachusetts, on
December 23, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E5–8099 Filed 12–29–05; 8:45 am]
BILLING CODE 4910–13–P
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Minerals Management Service
30 CFR Part 285
RIN 1010–AD30
Alternate Energy-Related Uses on the
Outer Continental Shelf
Minerals Management Service
(MMS), Interior.
ACTION: Advance Notice of Proposed
Rulemaking (ANPR).
AGENCY:
SUMMARY: The MMS is seeking
comments on the development of a
regulatory program to implement
portions of the Energy Policy Act of
2005, Section 388—Alternate EnergyRelated Uses on the Outer Continental
Shelf. Specifically, MMS is seeking
comments regarding energy
development from sources other than oil
and gas and alternate uses of existing
facilities.
DATES: MMS will consider all comments
received by February 28, 2006. MMS
will begin reviewing comments then
and may not fully consider comments
received after February 28, 2006.
ADDRESSES: You may submit comments
on the notice by any of the following
methods listed below. Please use the
Regulation Identifier Number (RIN)
‘‘1010–AD30’’ as an identifier in your
message. See also Public Comment
Policy under Supplementary
Information.
• MMS’s Public Connect on-line
commenting system, https://
ocsconnect.mms.gov. Follow the
instructions on the website for
submitting comments.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions on the Web site for
submitting comments.
• E-mail MMS at
rules.comments@mms.gov. Use the RIN
in the subject line.
E:\FR\FM\30DEP1.SGM
30DEP1
]]>Agencies
[Federal Register Volume 70, Number 250 (Friday, December 30, 2005)]
[Proposed Rules]
[Pages 77342-77345]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E5-8099]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 /
Proposed Rules
[[Page 77342]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-30-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -
217A, -217C, and -219 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 (PW) JT8D-209, -217, -217A, -217C,
and -219 turbofan engines. That AD currently requires initial and
repetitive visual inspections for fretting and fluorescent magnetic
particle inspections (FMPI) for cracking in the area of the tierod
holes on 8th stage high pressure compressor (HPC) front hubs (from here
on, referred to as HPC front hubs) that have operated at any time with
PWA 110-21 coating. This proposed AD would require either replacing HPC
front hubs and HPC disks that have operated at any time with PWA 110-21
coating and that operated in certain engine models, or, visually
inspecting and FMPI for cracking of those parts and replating them if
they pass inspection. This proposed AD would also require adding JT8D-
1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, 17A, 17R, and
17AR engines to the applicability. This proposed AD results from an
investigation by PW, which concluded that any HPC front hub or HPC disk
coated with PWA 110-21 that ever operated on JT8D-15, -15A, -17, -17A,
-17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines, could
crack before reaching their published life limit. We are proposing this
AD to prevent a rupture of an HPC front hub or an HPC disk that could
result in an uncontained engine failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by February 28,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2001 NE-30-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108,
telephone (860) 565-7700; fax (860) 565-1605 for the service
information identified in this proposed AD.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
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:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2001-NE-30-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 proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed 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 proposed AD in light of those
comments.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and any final disposition by appointment, between 8 a.m. and
4:30 p.m., Monday through Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On November 15, 2002, we issued AD 2002-23-14, Amendment 39-12958
(67 FR 70686, November 26, 2002). That AD requires initial and
repetitive visual inspections for fretting and FMPI for cracking in the
area of the tierod holes on HPC front hubs that have operated at any
time with PWA 110-21 coating. That AD resulted from the discovery of
cracking in the area of the tierod holes, found during routine engine
overhauls. That condition, if not corrected, could result in an
uncontained engine failure and damage to the airplane.
Actions After We Issued AD 2002-23-14
After we issued AD 2002-23-14, PW completed their investigation to
determine the cause of cracking in the area of the tierod holes on HPC
front hubs. As part of that investigation, PW looked at seven HPC front
hubs coated with PWA 110-21. They found fretting, cracks, or both, at
the rear bolt face of the HPC front hub on six of the seven HPC front
hubs. This was similar to the cracks seen in PW's initial investigation
into this issue. Most of the seven hubs had low cycle time, with the
lowest being 2,800 cycles-since-new. Additional cracks were found on
other stages of HPC disks, both with nickel-cadmium, and PWA 110-21
coating. PW determined that all HPC front hubs and HPC disks that have
ever been coated with PWA 110-21 and that have ever been operated on
JT8D-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -
219 turbofan engines, have a higher risk of fracturing before reaching
their published life limit of 20,000 cycles-in-service, than HPC front
hubs and HPC disks plated with nickel-cadmium.
Relevant Service Information
We have reviewed and approved the technical contents of PW Alert
Service Bulletin (ASB) No. JT8D A6430, Revision 2, dated December 23,
2004, applicable to JT8D-209, -217, -217A,
[[Page 77343]]
-217C, and -219 turbofan engines, and PW ASB No. JT8D A6468, dated
December 23, 2004, applicable to JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -
9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. Those
ASBs describe procedures for visual inspections for fretting wear and
FMPI for cracking of HPC front hubs that have operated with PWA 110-21
coating in the interface between the HPC front hub and the stage 8-9
spacer. Those ASBs also describe procedures for replating HPC front
hubs using nickel-cadmium, and replating stage 8-9 spacers using
nickel-cadmium or electroless nickel.
Differences Between the Proposed AD and the Manufacturer's Service
Information
Although the ASBs only require inspection of the HPC front hubs and
stage 8-9 spacers, we propose to require inspecting all 7th stage HPC
disks and 9th stage-through-12th stage HPC disks for fretting wear and
FMPI for cracking at the same time the HPC front hub is visually
inspected. These other HPC disks, which are coated with PWA 110-21,
have increased risk of cracking and failure.
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. We are proposing this AD, which would
require:
Visual inspections for fretting wear and FMPI of HPC front
hubs, HPC disks, and stage 8-9 spacers that at any time operated coated
with PWA 110-21, replacing them if necessary; replating those HPC front
hubs and disks using nickel-cadmium, and replating stage 8-9 spacers
using nickel-cadmium or electroless nickel;
OR
As optional terminating action to the visual inspections
in the proposed AD, replacing HPC front hubs, HPC disks, and stage 8-9
spacers that at any time operated coated with PWA 110-21 in JT8D-15, -
15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, or -219 turbofan
engines.
Replacement must be with HPC front hubs and HPC disks
plated with nickel-cadmium that have never operated with PWA 110-21
coating, and stage 8-9 spacers plated with nickel-cadmium or
electroless nickel.
The proposed AD would require that you do these actions using the
service information described previously.
Costs of Compliance
About 1,573 JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -
15A, -17, -17A, -17R, and -17AR turbofan engines, and 1,280 JT8D-200
series turbofan engines, installed on airplanes of U.S. registry would
be affected by this proposed AD. We estimate it would take about 12
work hours per engine to perform the proposed actions, and the average
labor rate is $65 per work hour. We also estimate 175 of those engines
would be removed before reaching scheduled maintenance, and would
require an additional 60 work hours to disassemble and reassemble each
engine. Based on these figures, we estimate the total cost of the
proposed AD to U.S. operators to be $2,907,840.
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
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 110-2134, 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 summary of the costs to comply with this proposal 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. 2001-NE-30-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, 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 39-12958 (67 FR
70686, November 26, 2002) and by adding a new airworthiness directive
to read as follows:
Pratt & Whitney: Docket No. 2001-NE-30-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by February 28,
2006.
Affected ADs
(b) This AD supersedes AD 2002-23-14, Amendment 39-12958.
Applicability
(c) This AD applies to all Pratt & Whitney (PW) JT8D-1, -1A, -
1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -
209, -217, -217A, -217C, and -219 turbofan engines, with 8th stage
high pressure compressor (HPC) front hubs (from here on, referred to
as HPC front hubs) as defined in the following Table 1:
Table 1.--AD Applicability
------------------------------------------------------------------------
And the HPC front hub: Then this AD is:
If:
------------------------------------------------------------------------
(1) The HPC front hub at any Operated in a JT8D-15, Applicable.
time operated coated with PWA -15A, -17, -17R, -
110-21. 17AR, -209, -217, -
217A, -217C, or -219
engine.
[[Page 77344]]
(2) The HPC front hub at any Operated in a JT8D- Applicable.
time had coating in the 209, -217, -217A, -
interface between the HPC 217C, or -219 engine.
front hub and the stage 8-9
spacer (PWA 110-21 coating
applied to spacer).
(3) The HPC front hub and HPC Operated in a JT8D-1, - Not applicable.
disks have PWA 110-21 1A, -1B, -7, -7A, -
coating. 7B, -9, -9A, or -11
engine, but never
operated in a JT8D-
15, -15A, -17, -17A, -
17R, -17AR, -209, -
217, -217A, -217C, or
-219 engine.
(4) The HPC front hub has ...................... Not applicable.
never operated with PWA 110-
21 coating in the interface
with the stage 8-9 spacer,
either on the HPC front hub
or on the stage 8-9 spacer.
------------------------------------------------------------------------
These engines are installed on, but not limited to, Boeing DC-9,
MD-80 series, 727 series, and 737 series airplanes.
Unsafe Condition
(d) This AD results from an investigation by PW, which concluded
that any HPC front hub or HPC disk coated with PWA 110-21 that ever
operated on JT8D-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -
217A, -217C, and -219 turbofan engines, could crack before reaching
their published life limit. We are issuing this AD to prevent a
rupture of an HPC front hub or an HPC disk that 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.
JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -
17R, and -17AR Turbofan Engines--Inspect or Replace HPC Front Hubs, HPC
Disks, and Stage 8-9 Spacers
(f) For JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A,
-17, -17A, -17R, and -17AR turbofan engines, do the following:
(1) Using the inspection schedule in Table 2 of this AD, strip
the protective coating, visually inspect for fretting wear,
fluorescent magnetic particle inspect (FMPI) for cracks, reidentify,
replate HPC front hubs and stage 8-9 spacers, and replace if
necessary.
(2) Use paragraphs 1 through 3.B.(7)(b) under ``For Rear
Compressor Front Hubs that Have Operated With PWA 110-21 coating AT
ANY TIME During Their Service Life in JT8D-15, -15A, -17, -17A, -
17R, -17AR Engine Models.'' of PW Alert Service Bulletin (ASB) JT8D
A6468, dated December 23, 2004.
Table 2.--HPC Disk Inspection Schedule
------------------------------------------------------------------------
Inspect before Also inspect 7th
HPC front hub cycles-since-new additional cycles- stage HPC disks
(CSN) on the effective date of in-service (CIS) and 9th stage-
this AD or CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more 500 CIS or 20,000 Paragraph (f)(3)
CSN of this AD
(ii) 15,500 or more, but fewer 1,000 CIS or Paragraph (f)(3)
than 19,000. 19,500 CSN. of this AD.
(iii) Fewer than 15,500. 5,000 CIS or Paragraph (f)(3)
16,500 CSN. of this AD.
(iv) Fewer than 5,000 that are .................. Paragraph (f)(3)
accessible. of this AD. If
the parts pass
inspection, parts
may be
reinstalled.
Inspect again
using the
criteria listed
in (iii) of this
Table.
------------------------------------------------------------------------
(3) When the HPC front hub is inspected, visually inspect for
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th
stage-through-12th stage HPC disks. Inspection information can be
found in the applicable sections of JT8D Engine Manual Part Number
(P/N) 481672, listed in the following Table 3:
Table 3.--7th Stage HPC Disks and 9th Stage-Through-12th Stage HPC Disks
Inspection Information
------------------------------------------------------------------------
Chapter/ Visual Fretting
Stage Section inspection inspection FMPI
------------------------------------------------------------------------
7..... 72-36-41 Inspection-01... Inspection-04... Inspection-03.
9..... 72-36-43 Inspection-01... Inspection-04... Inspection-03.
10.... 72-36-44 Inspection-01... Inspection-04... Inspection-03.
11.... 72-36-45 Inspection-01... Inspection-04... Inspection-03.
12.... 72-36-46 Inspection-01... Inspection-04... Inspection-03.
------------------------------------------------------------------------
JT8D-15, -15A, -17, -17A, -7R, and -17AR Turbofan Engines--Cycle
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium
Plating and PWA 110-21 Coating
(g) For JT8D-15, -15A, -17, -17A, -17R, and -17AR turbofan
engines with front hubs that entered service with nickel-cadmium
plating and PWA 110-21 coating, but have also operated during the
life of the hub with PWA 110-21 coating:
(1) You are allowed to make a cycle adjustment if the hub was
never operated with a PWA 110-21-coated stage 8-9 spacer.
(2) Use the information under ``Compliance'' of PW ASB JT8D
A6468, dated December 23, 2004, to determine the adjustment.
JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Inspect or
Replace HPC Front Hubs and Stage 8-9 Spacers
(h) For JT8D-209, -217, -217A, -217C, and -219 turbofan engines,
do the following:
[[Page 77345]]
(1) Using the inspection schedule in Table 4 of this AD, strip
the protective coating, visually inspect for fretting wear, FMPI for
cracking, reidentify, replate HPC front hubs and the stage 8-9
spacers, and replace if necessary.
(2) Use paragraphs 1. through 1.A. and paragraphs 2 through
2.C.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430,
Revision 2, dated December 23, 2004.
Table 4.--HPC Disk Inspection Schedule
------------------------------------------------------------------------
Also inspect 7th
Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (h)(3)
CSN. of this AD.
(ii) 15,500 or more, but fewer 1,000 CIS or Paragraph (h)(3)
than 19,000. 19,500 CSN. of this AD.
(iii) Fewer than 15,500......... 5,000 CIS or Paragraph (h)(3)
16,500 CSN. of this AD.
(iv) Fewer than 5,000 that are .................. Paragraph (h)(3)
accessible. of this AD. If
the parts pass
inspection, parts
may be
reinstalled.
Inspect again
using the
criteria listed
in (iii) of this
Table.
------------------------------------------------------------------------
(3) When the HPC front hub is inspected, visually inspect for
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th
stage through 12th stage HPC disks. Inspection information can be
found in the applicable sections of JT8D-200 Engine Manual P/N
773128, listed in Table 3 of this AD.
JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Cycle
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium
Plating and PWA 110-21 Coating
(i) For JT8D-209, -217, -217A, -217C, and -219 turbofan engines
with HPC front hubs that entered service with nickel-cadmium
plating, but have also operated during the life of the hub with PWA
110-21 coating:
(1) You are allowed to make a cycle adjustment.
(2) Use the information under ``CONDITION A'' of PW ASB JT8D
A6430, Revision 2, dated December 23, 2004, to determine the
adjustment.
Replacement of HPC Front Hubs and Stage 8-9 Spacers That Have Operated
With PWA 110-21 Coating, As Optional Terminating Action--All Engines
(j) For all applicable engines, as optional terminating action
for the repetitive visual inspections in this AD, replace HPC front
hubs and stage 8-9 spacers that have operated with PWA 110-21
coating in the interface between the hub and the stage 8-9 spacer
and HPC disks currently coated with PWA 110-21, as follows:
(1) Install a nickel-cadmium plated HPC front hub that has never
operated with PWA 110-21 coating in the interface between the HPC
front hub and the stage 8-9 spacer.
(2) Install a nickel-cadmium plated or electroless nickel-plated
stage 8-9 spacer.
(3) Install HPC disks that have never operated with PWA 110-21
coating.
Prohibition Against Recoating the HPC Front Hub, Stage 7 HPC Disk, and
Stage 8-9 Spacer With PWA 110-21--All Engines
(k) Do not recoat the HPC front hub with PWA 110-21 (Repair-23
of Chapter/Section 72-36-42 of JT8D-200 Engine Manual, P/N 773128,
and Repair-27 and Repair-28 of Chapter/Section 72-36-42 of JT8D
Engine Manual, P/N 481672).
(l) Do not recoat the 7th stage disk with PWA 110-21 (Repair-15
of Chapter/Section 72-36-41 of JT8D-200 Engine Manual, P/N 773128,
and Repair-15 of Chapter/Section 72-36-41 of JT8D Engine Manual, P/N
481672).
(m) Do not recoat the stage 8-9 spacer with PWA 110-21 (Repair-
03, Task 72-36-12-30-003-002, of Chapter/Section 72-36-12 of JT8D-
200 Engine Manual, P/N 773128, and Repair-01, Task 72-36-12-30-001-
002, of Chapter/Section 72-36-12 of JT8D Engine Manual, P/N 481672).
Definitions
(n) For the purposes of this AD, a shop visit is an engine
removal, where engine maintenance entails separating pairs of major
engine flanges or removing a disk, hub, or spool at a maintenance
facility, regardless of other planned maintenance, except as
follows:
(1) Removing the engine to perform field maintenance type
activities at a maintenance facility in lieu of performing them on-
wing is not a ``shop visit.''
(2) Separating flanges of the Combustion Chamber and Turbine Fan
Duct Assembly (split flanges) to access non-rotating accessory
hardware is not a ``shop visit.''
(3) Separating flanges to ship the engine without subsequent
internal maintenance is not a ``shop visit.''
(o) For the purposes of this AD accessibility of the HPC front
hub is removing the hub from the engine and deblading that hub.
Alternative Methods of Compliance
(p) 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.
Related Information
(q) None.
Issued in Burlington, Massachusetts, on December 23, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E5-8099 Filed 12-29-05; 8:45 am]
BILLING CODE 4910-13-P
