Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes, 61723-61727 [05-21255]
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Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–22757;
Directorate Identifier 2005–SW–32–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of our docket web site,
you can find and read the comments to
any of our dockets, including the name
of the individual who sent the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78), or you may visit
https://dms.dot.gov.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to 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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Regulatory Findings
Authority: 49 U.S.C. 106(g), 40113, 44701.
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 an economic evaluation
of the estimated costs to comply with
this AD. See the DMS to examine the
economic evaluation.
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
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§ 39.13
[Amended]
61723
Perform the torque test and the additional
torque procedures as stated in the
Accomplishment Instructions, paragraph
3.B.(1) through 3.B.(3) of the ASB. The torque
test is not required at the recurring
inspection intervals of the lower bifilar arm
assembly.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Boston Aircraft
Certification Office, FAA, for information
about previously approved alternative
methods of compliance.
(c) Inspect the lower bifilar arm assembly
and perform the torque test by following the
specified portions of Sikorsky Alert Service
Bulletin No. 76–65–62, dated December 14,
2004. The Director of the Federal Register
approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager,
Commercial Tech Support, 6900 Main Street,
Stratford, Connecticut 06614, phone (203)
386–3001, fax (203) 386–5983. Copies may be
inspected at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(d) This amendment becomes effective on
November 10, 2005.
Issued in Fort Worth, Texas, on October 17,
2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–21256 Filed 10–25–05; 8:45 am]
BILLING CODE 4910–13–P
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
2005–22–01 Sikorsky Aircraft Corporation:
Amendment 39–14345. Docket No.
FAA–2005–22757; Directorate Identifier
2005–SW–32–AD.
Applicability: Model S–76A, B, and C, with
a main rotor hub pilot fitting (pilot fitting),
part number (P/N) 76103–08003–101, with
1500 or more hours time-in-service (TIS),
installed, certificated in any category.
Compliance: Required as indicated.
To prevent failure of a bifilar lug, damage
to the main rotor system, and subsequent loss
of control of the helicopter, accomplish the
following:
(a) Within 50 hours TIS, and thereafter at
intervals not to exceed 50 hours TIS, inspect
the lower bifilar arm assembly for a crack in
the lug attachment area. Conduct the
inspection of the lower bifilar arm assembly
by following the Accomplishment
Instructions, paragraph 3.A.(1) through
3.A.(6), of Sikorsky Alert Service Bulletin No.
76–65–62, dated December 14, 2004 (ASB).
(1) If you find a crack on any bifilar arm
assembly lug, before further flight, replace
the bifilar arm assembly with an airworthy
bifilar arm assembly.
(2) If no crack is found at the initial
inspection, perform a one-time torque test.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22018; Directorate
Identifier 2005–CE–41–AD; Amendment 39–
14348; AD 2005–22–04]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Models PC–12 and PC–12/
45 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Models
PC–12 and PC–12/45 airplanes. This AD
requires you to determine (maintenance
records check and/or inspection)
whether certain nose landing gear
(NLG), main landing gear (MLG), and
MLG shock absorber assemblies with a
serial number beginning with ‘‘AM’’ are
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Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations
installed, and, if installed, would
require you to replace them with ones
without the ‘‘AM.’’ This AD is the result
of mandatory continuing airworthiness
information (MCAI) issued by the
airworthiness authority for Switzerland.
We are issuing this AD to detect and
correct the NLG, MLG, and MLG shock
absorber assemblies that are affected by
hydrogen embrittlement, which could
result in failure of the landing gear. This
failure could lead to nose or main
landing gear collapse during operation
with consequent loss of airplane
control.
This AD becomes effective on
December 12, 2005.
As of December 12, 2005, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
DATES:
To get the service
information identified in this AD,
contact Pilatus Aircraft Ltd., Customer
Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619
6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com
or from Pilatus Business Aircraft Ltd.,
Product Support Department, 11755
Airport Way, Broomfield, Colorado
80021; telephone: (303) 465–9099;
facsimile: (303) 465–6040.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2005–22018; Directorate Identifier
2005–CE–41–AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
Comments
What events have caused this AD?
The Federal Office for Civil Aviation
(FOCA), which is the airworthiness
authority for Switzerland, recently
notified FAA that an unsafe condition
may exist on Pilatus Models PC–12 and
PC–12/45 airplanes. The FOCA reports
that some components of the main
landing gear (MLG), nose landing gear
(NLG), and MLG shock absorber
assemblies have the potential to fail
during operation.
Investigations revealed that an
improper cadmium plating process
applied to the high strength steel part
causes the problem. This can result in
hydrogen embrittlement. Affected are
only components that are installed on
MLG, NLG, and MLG shock absorber
assemblies, with serial numbers that
start with the letters ‘‘AM.’’ Components
in this condition can experience a
decreased fatigue life.
What is the potential impact if FAA
took no action? Failure of the nose or
main landing gear could lead to nose or
main landing gear collapse during
operation with consequent loss of
airplane control.
Has FAA taken any action to this
point? We issued a proposal to amend
part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to certain
Pilatus Aircraft Ltd. (Pilatus) Models
PC–12 and PC–12/45 airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on August 22, 2005
(70 FR 48914). The NPRM proposed to
require you to determine (maintenance
records check and/or inspection)
whether certain nose landing gear
(NLG), main landing gear (MLG), and
MLG shock absorber assemblies with a
serial number beginning with ‘‘AM’’ are
installed, and, if installed, would
require you to replace them with ones
without the ‘‘AM.’’
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD. We
received no comments on the proposal
or on the determination of the cost to
the public.
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
—Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
—Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. 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.
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
350 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to do the check of the logbook to
identify NLG, MLG, and MLG shock
absorber assemblies with serial numbers
that start with the letters AM:
Total cost per
airplane
Labor cost
Parts cost
1 work hour × $65 per hour = $65 ....................................................
Not applicable .............................
We estimate the following costs to do
any necessary inspection and
replacement of all possible NLG, MLG,
and MLG shock absorber assemblies that
would be required based on the results
of this check of the logbook. We have no
Labor cost
$3,800 for the NLG kit, $850 for the MLG kit,
and $2,600 for the MLG shock absorber assembly kit.
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350 × $65 = $22,750.
way of determining the number of
airplanes that may need this
replacement:
Parts cost
41 work hours × $65 per hour = $2,665 ............
$65
Total cost on U.S.
operators
Total cost per airplane
$2,665 + $3,800 + $850 + $2,600 = $9,915.
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Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations
Pilatus will provide warranty credit
for replacing the specified assemblies to
the extent stated in the service
information.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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 AD.
Regulatory Findings
Will this AD impact various entities?
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.
Will this AD involve a significant rule
or regulatory action? 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 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 other
information as included in the
Regulatory Evaluation) 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 ‘‘Docket No. FAA–2005–22018;
Directorate Identifier 2005–CE–41–AD’’
in your request.
61725
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by adding a
new AD to read as follows:
2005–22–04 Pilatus Aircraft Ltd.:
Amendment 39–14348; Docket No.
FAA–2005–22018; Directorate Identifier
2005–CE–41–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on December
12, 2005.
What Other ADs Are Affected by This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models PC–12 and PC–
12/45 airplanes, manufacturer serial numbers
(MSN) 101 through MSN 625, that are
certificated in any category.
List of Subjects in 14 CFR Part 39
What Is the Unsafe Condition Presented in
This AD?
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(d) This AD is the result of mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Switzerland. The actions specified in this AD
are intended to detect and correct the nose
landing gear (NLG), main landing gear
(MLG), and MLG shock absorber assemblies
that are affected by hydrogen embrittlement,
which could result in failure of the landing
gear. This failure could lead to nose or main
landing gear collapse during operation with
consequent loss of airplane control.
Adoption of the Amendment
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
What Must I Do To Address This Problem?
1. The authority citation for part 39
continues to read as follows:
I
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Maintenance Records Check:
(i) For MSN 101 through MSN 471 and MSN 473 through MSN 482:
Check the maintenance records to determine whether the following
replacements have been made:
(A) Nose landing gear (NLG) assemblies, part number (P/N)
532.20.12.038 and P/N 532.20.12.039 with serial numbers (S/N) AM
001 through AM 045 and AM 048 through AM 054;
(B) Main landing gear (MLG) assemblies, P/N 532.10.12.049 and P/N
532.10.12.050 with S/N AM 001 through AM 027, AM 029 through
AM 045, AM 047 through AM 050, AM 052, and AM 053; and
(C) MLG shock absorber assemblies, P/N 532.10.12.175, with S/N AM
001 through AM 017, AM 019, AM 021 through AM 063, AM 065
through AM 070, AM 072 through AM 074, AM 080, AM 084, AM
086, AM 089, AM 090, AM 093 through AM 096, AM 099, AM 103
through AM 107.
(ii) For MSN 472 and MSN 483 through MSN 625: Verify that the S/N
parts identified in paragraphs (e)(1)(i)(A), (e)(1)(i)(B), and (e)(1)(i)(C)
of this AD have not been installed.
(iii) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14
CFR 43.7) may make this check. You must make an entry into the
aircraft records that shows compliance with this portion of the AD in
accordance with section 43.9 of the Federal Aviation Regulations
(14 CFR 43.9).
Within the next 100 hours time-inservice (TIS) or 12 calendar
months after December 12,
2005 (the effective date of this
AD), whichever occurs first, unless already done..
No special procedures necessary
to check the maintenance
records.
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Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations
Actions
Compliance
Procedures
(2) If you find as a result of the check required by paragraph (e)(1)(i)
of this AD that there is no record of the specified assembly replacement, or as a result of the check required by paragraph (e)(1)(ii) of
this AD that parts have been installed in service, then inspect:
(i) The NLG assemblies, P/N 532.20.12.038 and P/N 532.20.12.039,
for any S/N that starts with AM 001 through AM 045 and AM 048
through AM 054.
(ii) The MLG assemblies, P/N 532.10.12.049 and P/N 532.10.12.050,
for any S/N that starts with AM 001 through AM 027, AM 029
through AM 045, AM 047 through AM 050, AM 052, and AM 053.
(iii) The MLG shock absorber assemblies, P/N 532.10.12.175, for any
S/N that starts with AM 001 through AM 017, AM 019, AM 021
through AM 063, AM 065 through AM 070, AM 072 through AM
074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through
AM 096, AM 099, and AM 103 through AM 107.
(iv) You may choose to do the inspection without doing the maintenance records check.
Within the next 100 hours time-inservice (TIS) or 12 calendar
months after December 12,
2005 (the effective date of this
AD), whichever occurs first, unless already done..
Follow Pilatus PC12 Service Bulletin No. 32–016, dated March
11, 2004.
(3) If during the inspection required by paragraph (e)(2) of this AD,
you find:
(i) Any NLG assembly, P/N 532.20.12.038 and P/N 532.20.12.039,
with any S/N that starts with AM 001 through AM 045 or AM 048
through AM 054, replace the NLG specific components with new
components.
(ii) Any MLG assembly, P/N 532.10.12.049 and P/N 532.10.12.050,
with any S/N that starts with AM 001 through AM 027, AM 029
through AM 045, AM 047 through AM 050, AM 052, or AM 053, replace the MLG specific components with new components.
(iii) Any MLG shock absorber assembly, P/N 532.10.12.175, with any
S/N that starts with AM 001 through AM 017, AM 019, AM 021
through AM 063, AM 065 through AM 070, AM 072 through AM
074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through
AM 096, AM 099, or AM 103 through AM 107, replace the MLG
shock absorber specific components with new components.
Before further flight after the inspection required by paragraph
(e)(2) of this AD.
Follow Pilatus PC12 Service Bulletin No. 32–016, dated March
11, 2004.
(4) Do not install:
(i) Any NLG assembly, P/N 532.20.12.038 and P/N 532.20.12.039,
with any S/N that starts with AM 001 through AM 045 or AM 048 effective through AM 054.
(ii) Any MLG assembly, P/N 532.10.12.049 and P/N 532.10.12.050,
with any S/N that starts with AM 001 through AM 027, AM 029
through AM 045, AM 047 through AM 050, AM 052, or AM 053.
(iii) Any MLG shock absorber assembly, P/N 532.10.12.175, with any
S/N that starts with AM 001 through AM 017, AM 019, AM 021
through AM 063, AM 065 through AM 070, AM 072 through AM
074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through
AM 096, AM 099, or AM 103 through AM 107.
As of December 12, 2005 (the effective date of this AD)
Not Applicable.
Note 1: AD 2002–14–22, issued on July 8,
2002 (67 FR 46582), and AD 2004–06–05,
issued on March 15, 2004 (69 FR 13712), are
still applicable.
City, Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
Note 2: The FAA recommends that you
send any removed parts or assemblies to
Pilatus.
(g) Swiss AD Number HB–2005–168, dated
May 3, 2005, also addresses the subject of
this AD.
May I Request an Alternative Method of
Compliance?
Does This AD Incorporate Any Material by
Reference?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Standards Office, Small Airplane
Directorate, FAA. For information on any
already approved alternative methods of
compliance, contact Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas
(h) You must do the actions required by
this AD following the instructions in Pilatus
PC12 Service Bulletin No. 32–016, dated
March 11, 2004. 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. To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
Customer Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 6208;
facsimile: +41 41 619 7311; e-mail:
SupportPC12@pilatus-aircraft.com or from
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Is There Other Information That Relates to
This Subject?
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Pilatus Business Aircraft Ltd., Product
Support Department, 11755 Airport Way,
Broomfield, Colorado 80021; telephone: (303)
465–9099; facsimile: (303) 465–6040. To
review copies of this service information, go
to the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–22018; Directorate Identifier 2005–CE–
41–AD.
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Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations
Issued in Kansas City, Missouri, on
October 19, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–21255 Filed 10–25–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20692; Directorate
Identifier 2004–NM–229–AD; Amendment
39–14350; AD 2005–22–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–
200F, 747–300, 747SR, and 747SP series
airplanes. This AD requires doing a onetime high-frequency eddy current
inspection and repetitive detailed
inspections for cracks in the frame web
of main entry door number 1; and
repairing the door frame web if
necessary. This AD also provides for
optional terminating action for the
repetitive inspections. This AD is
prompted by reports of cracking at the
upper aft corner of the cutout for main
entry door number 1 in the station 488
frame web. We are issuing this AD to
detect and correct cracks in the frame
web. These cracks could cause the frame
to break and lead to rapid
decompression of the airplane.
DATES: This AD becomes effective
November 30, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of November 30, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
VerDate Aug<31>2005
14:58 Oct 25, 2005
Jkt 208001
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20692; the directorate
identifier for this docket is 2004–NM–
229–AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–
200B, 747–200C, 747–200F, 747–300,
747SR, and 747SP series airplanes. That
action, published in the Federal
Register on March 23, 2005 (70 FR
14589), proposed to require doing a onetime high-frequency eddy current
inspection and repetitive detailed
inspections for cracks in the frame web
of main entry door number 1; and
repairing the door frame web if
necessary. That action also proposed to
provide for optional terminating action
for the repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Request To Include Optional Inspection
One commenter requests that we
include an option for Group 3 airplanes
in paragraph (f) of the proposed AD to
perform an open-hole high-frequency
eddy current (HFEC) inspection every
3,000 flight cycles instead of a detailed
inspection every 1,500 flight cycles. The
commenter states that the manufacturer
has found this optional inspection to be
structurally acceptable.
We agree with the commenter that
performing an HFEC inspection every
3,000 flight cycles would provide an
equivalent level of safety as intended by
this AD. However, the repetitive
detailed inspection requirement is
actually specified in paragraph (g) of the
proposed AD, not paragraph (f).
Therefore, we have revised paragraph
(g) of the final rule, for Group 3
airplanes only, to include an option to
perform a surface HFEC inspection of
the frame web between the upper door
sill and door stop number 8 for cracks
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
61727
every 3,000 flight cycles in accordance
with the method referenced in Figure 3
or Figure 4 of the Accomplishment
Instructions of Boeing Alert Service
Bulletin (ASB) 747–53A2508, dated
August 19, 2004.
Request To Revise Frame Inner Chord
Inspection Requirement
One commenter requests that we
delete paragraph (j) of the proposed AD
or revise it to state that when the frame
inner chord is being replaced
concurrently with the required frame
web repairs, the open-hole HFEC
inspection of the frame inner chord is
not required. The commenter states that
the intent of paragraph (j) should be that
when the frame inner chord is being
replaced, there is no need to inspect the
existing fastener holes in the chord
because the chord is a new part. The
commenter refers to the applicable
Boeing Structural Repair Manual (SRM)
and Boeing ASB 747–53A2508 to
support this contention.
We agree with this request. Open-hole
HFEC inspection of the frame inner
chord is a conditional inspection
included in the repair procedures
specified in paragraph (h) of this AD.
However, AD 91–11–01, amendment
39–6997 (dated May 15, 1991),
referenced in paragraph (j) of the
proposed AD, only requires inspecting
the frame inner chord, while AD 90–06–
06, amendment 39–6490 (dated March
7, 1990), actually requires replacing the
frame inner chord. Therefore, we have
concluded that paragraph (j) of the
proposed AD should have referred to
AD 90–06–06, rather than AD 91–11–01,
regarding concurrent replacement of the
frame inner chord. We have revised
paragraph (j) of the final rule to reflect
the commenter’s request and to
correctly refer to AD 90–06–06. Further,
to ensure that there is no confusion
about the HFEC inspection, we also
revised paragraph (h) of the final rule to
include a reference to an ‘‘open-hole’’
HFEC inspection.
Request To Clarify Use of Structural
Repair Manual
The same commenter requests that
paragraph (h) of the proposed AD be
clarified. The commenter asserts that
paragraph (h) should be revised to state
that the Boeing SRM meets the intent of
the proposed AD. Further, the
commenter requests that we clarify the
statement ‘‘For a repair method to be
approved, the approval must
specifically reference this AD.’’ The
commenter feels that paragraph (h) as
written might lead to confusion.
We agree with the commenter that the
Boeing SRM procedures specified in the
E:\FR\FM\26OCR1.SGM
26OCR1
]]>Agencies
[Federal Register Volume 70, Number 206 (Wednesday, October 26, 2005)]
[Rules and Regulations]
[Pages 61723-61727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21255]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22018; Directorate Identifier 2005-CE-41-AD;
Amendment 39-14348; AD 2005-22-04]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes.
This AD requires you to determine (maintenance records check and/or
inspection) whether certain nose landing gear (NLG), main landing gear
(MLG), and MLG shock absorber assemblies with a serial number beginning
with ``AM'' are
[[Page 61724]]
installed, and, if installed, would require you to replace them with
ones without the ``AM.'' This AD is the result of mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. We are issuing this AD to detect and correct the NLG,
MLG, and MLG shock absorber assemblies that are affected by hydrogen
embrittlement, which could result in failure of the landing gear. This
failure could lead to nose or main landing gear collapse during
operation with consequent loss of airplane control.
DATES: This AD becomes effective on December 12, 2005.
As of December 12, 2005, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business
Aircraft Ltd., Product Support Department, 11755 Airport Way,
Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303)
465-6040.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-22018; Directorate
Identifier 2005-CE-41-AD.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Federal Office for Civil
Aviation (FOCA), which is the airworthiness authority for Switzerland,
recently notified FAA that an unsafe condition may exist on Pilatus
Models PC-12 and PC-12/45 airplanes. The FOCA reports that some
components of the main landing gear (MLG), nose landing gear (NLG), and
MLG shock absorber assemblies have the potential to fail during
operation.
Investigations revealed that an improper cadmium plating process
applied to the high strength steel part causes the problem. This can
result in hydrogen embrittlement. Affected are only components that are
installed on MLG, NLG, and MLG shock absorber assemblies, with serial
numbers that start with the letters ``AM.'' Components in this
condition can experience a decreased fatigue life.
What is the potential impact if FAA took no action? Failure of the
nose or main landing gear could lead to nose or main landing gear
collapse during operation with consequent loss of airplane control.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to certain Pilatus Aircraft Ltd.
(Pilatus) Models PC-12 and PC-12/45 airplanes. This proposal was
published in the Federal Register as a notice of proposed rulemaking
(NPRM) on August 22, 2005 (70 FR 48914). The NPRM proposed to require
you to determine (maintenance records check and/or inspection) whether
certain nose landing gear (NLG), main landing gear (MLG), and MLG shock
absorber assemblies with a serial number beginning with ``AM'' are
installed, and, if installed, would require you to replace them with
ones without the ``AM.''
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. 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.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 350 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the check of
the logbook to identify NLG, MLG, and MLG shock absorber assemblies
with serial numbers that start with the letters AM:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65.... Not applicable......... $65 350 x $65 = $22,750.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary inspection and
replacement of all possible NLG, MLG, and MLG shock absorber assemblies
that would be required based on the results of this check of the
logbook. We have no way of determining the number of airplanes that may
need this replacement:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
41 work hours x $65 per hour $3,800 for the NLG $2,665 + $3,800 +
= $2,665. kit, $850 for the $850 + $2,600 =
MLG kit, and $2,600 $9,915.
for the MLG shock
absorber assembly
kit.
------------------------------------------------------------------------
[[Page 61725]]
Pilatus will provide warranty credit for replacing the specified
assemblies to the extent stated in the service information.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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 AD.
Regulatory Findings
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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 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
other information as included in the Regulatory Evaluation) 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 ``Docket
No. FAA-2005-22018; Directorate Identifier 2005-CE-41-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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2005-22-04 Pilatus Aircraft Ltd.: Amendment 39-14348; Docket No.
FAA-2005-22018; Directorate Identifier 2005-CE-41-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on December 12, 2005.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models PC-12 and PC-12/45 airplanes,
manufacturer serial numbers (MSN) 101 through MSN 625, that are
certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland. The actions specified in this AD are intended to detect
and correct the nose landing gear (NLG), main landing gear (MLG),
and MLG shock absorber assemblies that are affected by hydrogen
embrittlement, which could result in failure of the landing gear.
This failure could lead to nose or main landing gear collapse during
operation with consequent loss of airplane control.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Maintenance Records Check: Within the next No special
(i) For MSN 101 through MSN 471 100 hours time-in- procedures
and MSN 473 through MSN 482: service (TIS) or necessary to
Check the maintenance records 12 calendar check the
to determine whether the months after maintenance
following replacements have December 12, 2005 records.
been made:. (the effective
(A) Nose landing gear (NLG) date of this AD),
assemblies, part number (P/N) whichever occurs
532.20.12.038 and P/N first, unless
532.20.12.039 with serial already done..
numbers (S/N) AM 001 through AM
045 and AM 048 through AM 054;.
(B) Main landing gear (MLG)
assemblies, P/N 532.10.12.049
and P/N 532.10.12.050 with S/N
AM 001 through AM 027, AM 029
through AM 045, AM 047 through
AM 050, AM 052, and AM 053; and.
(C) MLG shock absorber .................. ..................
assemblies, P/N 532.10.12.175,
with S/N AM 001 through AM 017,
AM 019, AM 021 through AM 063,
AM 065 through AM 070, AM 072
through AM 074, AM 080, AM 084,
AM 086, AM 089, AM 090, AM 093
through AM 096, AM 099, AM 103
through AM 107.
(ii) For MSN 472 and MSN 483 .................. ..................
through MSN 625: Verify that
the S/N parts identified in
paragraphs (e)(1)(i)(A),
(e)(1)(i)(B), and (e)(1)(i)(C)
of this AD have not been
installed.
(iii) The owner/operator holding .................. ..................
at least a private pilot
certificate as authorized by
section 43.7 of the Federal
Aviation Regulations (14 CFR
43.7) may make this check. You
must make an entry into the
aircraft records that shows
compliance with this portion of
the AD in accordance with
section 43.9 of the Federal
Aviation Regulations (14 CFR
43.9).
---------------------------------
[[Page 61726]]
(2) If you find as a result of Within the next Follow Pilatus
the check required by paragraph 100 hours time-in- PC12 Service
(e)(1)(i) of this AD that there service (TIS) or Bulletin No. 32-
is no record of the specified 12 calendar 016, dated March
assembly replacement, or as a months after 11, 2004.
result of the check required by December 12, 2005
paragraph (e)(1)(ii) of this AD (the effective
that parts have been installed date of this AD),
in service, then inspect: whichever occurs
(i) The NLG assemblies, P/N first, unless
532.20.12.038 and P/N already done..
532.20.12.039, for any S/N that
starts with AM 001 through AM
045 and AM 048 through AM 054..
(ii) The MLG assemblies, P/N
532.10.12.049 and P/N
532.10.12.050, for any S/N that
starts with AM 001 through AM
027, AM 029 through AM 045, AM
047 through AM 050, AM 052, and
AM 053.
(iii) The MLG shock absorber
assemblies, P/N 532.10.12.175,
for any S/N that starts with AM
001 through AM 017, AM 019, AM
021 through AM 063, AM 065
through AM 070, AM 072 through
AM 074, AM 080, AM 084, AM 086,
AM 089, AM 090, AM 093 through
AM 096, AM 099, and AM 103
through AM 107.
(iv) You may choose to do the
inspection without doing the
maintenance records check.
---------------------------------
(3) If during the inspection Before further Follow Pilatus
required by paragraph (e)(2) of flight after the PC12 Service
this AD, you find: inspection Bulletin No. 32-
(i) Any NLG assembly, P/N required by 016, dated March
532.20.12.038 and P/N paragraph (e)(2) 11, 2004.
532.20.12.039, with any S/N of this AD.
that starts with AM 001 through
AM 045 or AM 048 through AM
054, replace the NLG specific
components with new components..
(ii) Any MLG assembly, P/N
532.10.12.049 and P/N
532.10.12.050, with any S/N
that starts with AM 001 through
AM 027, AM 029 through AM 045,
AM 047 through AM 050, AM 052,
or AM 053, replace the MLG
specific components with new
components..
(iii) Any MLG shock absorber
assembly, P/N 532.10.12.175,
with any S/N that starts with
AM 001 through AM 017, AM 019,
AM 021 through AM 063, AM 065
through AM 070, AM 072 through
AM 074, AM 080, AM 084, AM 086,
AM 089, AM 090, AM 093 through
AM 096, AM 099, or AM 103
through AM 107, replace the MLG
shock absorber specific
components with new components.
---------------------------------
(4) Do not install: As of December 12, Not Applicable.
(i) Any NLG assembly, P/N 2005 (the
532.20.12.038 and P/N effective date of
532.20.12.039, with any S/N this AD)
that starts with AM 001 through
AM 045 or AM 048 effective
through AM 054..
(ii) Any MLG assembly, P/N
532.10.12.049 and P/N
532.10.12.050, with any S/N
that starts with AM 001 through
AM 027, AM 029 through AM 045,
AM 047 through AM 050, AM 052,
or AM 053.
(iii) Any MLG shock absorber
assembly, P/N 532.10.12.175,
with any S/N that starts with
AM 001 through AM 017, AM 019,
AM 021 through AM 063, AM 065
through AM 070, AM 072 through
AM 074, AM 080, AM 084, AM 086,
AM 089, AM 090, AM 093 through
AM 096, AM 099, or AM 103
through AM 107.
------------------------------------------------------------------------
Note 1: AD 2002-14-22, issued on July 8, 2002 (67 FR 46582), and
AD 2004-06-05, issued on March 15, 2004 (69 FR 13712), are still
applicable.
Note 2: The FAA recommends that you send any removed parts or
assemblies to Pilatus.
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090.
Is There Other Information That Relates to This Subject?
(g) Swiss AD Number HB-2005-168, dated May 3, 2005, also
addresses the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Pilatus PC12 Service Bulletin No. 32-016, dated
March 11, 2004. 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. To get a copy of this
service information, contact Pilatus Aircraft Ltd., Customer Liaison
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208;
facsimile: +41 41 619 7311; e-mail: SupportPC12@pilatus-aircraft.com
or from Pilatus Business Aircraft Ltd., Product Support Department,
11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-
9099; facsimile: (303) 465-6040. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2005-22018;
Directorate Identifier 2005-CE-41-AD.
[[Page 61727]]
Issued in Kansas City, Missouri, on October 19, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-21255 Filed 10-25-05; 8:45 am]
BILLING CODE 4910-13-P
