[Federal Register: June 16, 2004 (Volume 69, Number 115)]
[Rules and Regulations]
[Page 33558-33561]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16jn04-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-CE-08-AD; Amendment 39-13670; AD 2004-12-11]
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.
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SUMMARY: The FAA adopts a new airworthiness directive (AD) for all
Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes.
This AD requires you to check the airplane logbook to determine whether
certain inboard and outboard flap flexshafts have been replaced with
parts of improved design. If the parts of improved design are not
installed, you are required to replace certain inboard and/or outboard
flap flexshafts with the parts of improved design. The pilot is allowed
to do the logbook check. If the pilot can positively determine that the
parts of improved design are installed, no further action is required.
This AD is the result of mandatory continuing airworthiness information
(MCAI) issued by the airworthiness authority for Switzerland. We are
issuing this AD to prevent rupture of the flap flexshafts due to
corrosion, which could cause the flap system to become inoperable.
DATES: This AD becomes effective on July 26, 2004.
As of July 26, 2004, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: You may get the service information identified in this AD
from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail: SupportPC12@pilaltus-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.
You may view the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2004-CE-08-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m.
to 4 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer,
[[Page 33559]]
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 all Pilatus
Models PC-12 and PC-12/45 airplanes equipped with an inboard and/or
outboard flap flexshaft, part numbers (P/N) 945.02.02.203 and/or
945.02.02.204. The FOCA reports several occurrences of corrosion found
on the inner drive cables of these flap flexshafts.
The FOCA determined that moisture from the pressurized cabin could
enter the flap flexshafts through the fittings of the protection hose
causing corrosion. This corrosion could cause the flap flexshafts to
rupture.
What is the potential impact if FAA took no action? If not
prevented, corrosion on the flap flexshafts could cause flap flexshafts
to rupture and lead to the flap system becoming inoperable.
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 all Pilatus Models PC-12 and PC-12/45
airplanes of the same type design that are equipped with an inboard
and/or outboard flap flexshaft, P/N 945.02.02.203 and/or P/N
945.02.02.204. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on April 9, 2004 (69 FR 18843).
The NPRM proposed to require you to check the airplane logbook to
determine whether certain inboard and outboard flap flexshafts have
been replaced with parts of improved design. If the parts of improved
design are not installed, you would be required to replace certain
inboard and/or outboard flap flexshafts with the parts of improved
design.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. The following
presents the comments received on the proposal and FAA's response to
each comment:
Comment Issue No. 1: Revise the Stated Result of the Unsafe Condition
What is the commenter's concern? The manufacturer states that
failure of the flap system will not lead to loss of control of the
airplane. The manufacturer explains that the flap computer (FCWU)
protects the system against asymmetric flap deployment with a failure
rate of 10E-9 in the event of a flexshaft rupture (and other failure
modes). The pilot has no possibility to override this protection.
The manufacturer wants us to state that rupture of the flap
flexshafts due to corrosion could cause the flap system to become
inoperative but does not result in loss of control of the airplane.
What is FAA's response to the concern? We agree with the
manufacturer. After reviewing additional information provided by the
FOCA of Switzerland about the result of the unsafe condition on the
flap flexshafts, we will change the final rule AD action based on this
comment.
Comment Issue No. 2: Change the Costs of Compliance Section
What is the commenter's concern? The manufacturer states that of
the 260 airplanes affected by this AD, only 65 need to have the
replacement parts installed. The manufacturer wants the cost of
compliance changed to reflect the cost of installing the replacement
parts for these 65 airplanes instead of all 260 airplanes.
The manufacturer has also agreed to cover the cost of replacement
parts for all airplanes even though the warranty credit period has
expired. The manufacturer also wants us to change the cost of
compliance to reflect this reduction.
What is FAA's response to the concern? We partially agree with the
manufacturer. We agree that there may be only 65 airplanes currently on
the United States (U.S.) registry that need to have the replacements
parts installed. However, because parts could have been replaced on an
airplane after it left the manufacturer, we used the total number of
affected airplanes in the Costs of Compliance section. We have no way
of determining the exact number of airplanes that will need to have the
replacements done.
We are not changing the final rule AD action based on this comment.
We are, however, adding a section to cover the cost for doing the
logbook check. Since all of the affected airplanes will probably not
need to have the replacement parts installed, a logbook check will have
to be done on all of the affected airplanes in order to make this
determination.
Comment Issue No. 3: Change Paragraph (e)(5)
What is the commenter's concern? The manufacturer states that the
language in paragraph (e)(5) prohibits you from ever installing any
version of the inboard and outboard flap flexshafts other than part
numbers (P/N) 945.02.02.205 and 945.02.02.206. Therefore, airplanes
manufactured in the future with a new design part number for the flap
flexshafts will be in automatic non-compliance with this AD.
The manufacturer wants this language changed to prohibit ever
installing P/Ns 945.02.02.203 and 945.02.02.204 but allows you to
install new flap flexshafts introduced in the future.
What is FAA's response to the concern? We agree with the commenter.
Preventing future installations of new design parts was not the intent
of this AD.
We will change the final rule AD action based on this comment.
Comment Issue No. 4: Withdraw the Proposed AD Action To Mandate
Compliance With Pilatus PC12 Service Bulletin No. 27-015
What is the commenter's concern? The manufacturer states that there
is no unsafe condition. The manufacturer further explains that the flap
computer (FCWC) protects the system against asymmetric flap deployment
with a failure rate of 10E-9 in the event of a flexshaft rupture (and
other failure modes). This failure does not result in loss of control
of the airplane and the pilot has no possibility to override this
protection.
The manufacturer also states that they can confirm that over 90
percent of the U.S. registered airplanes have already had the
replacement parts installed.
The manufacturer wants the proposed AD action withdrawn.
What is FAA's response to the concern? We do not agree that there
is no unsafe condition. We agree that approximately 90 percent of the
affected airplanes may have already had the replacement parts
installed. However, at least 10 percent of the affected airplanes still
need the replacement done. In addition, the only way to legally prevent
these unsafe parts from being installed in the future is through AD
action. This would include airplanes brought into the U.S. and put on
the U.S. registry.
Therefore, to ensure that all affected airplanes do not have the
unsafe parts installed, we are not changing the final rule AD action
based on this comment.
Comment Issue No. 5: Make the AD Serial Number Specific
What is the commenter's concern? The commenter states that the
manufacturer has been incorporating the new P/Ns in the production line
of new airplanes since 2003 making the
[[Page 33560]]
inclusion of airplanes produced after Manufacturer Serial Number (MSN)
489 illogical. Making the AD serial number specific speeds compliance
and makes everyone's life easier.
The commenter wants the AD changed to be serial number specific as
specified in Pilatus PC12 Service Bulletin No. 27-015.
What is FAA's response to the concern? We partially agree with the
commenter. We agree that serial number specific ADs are easier to
track; however, parts could be swapped from one of the earlier affected
models and installed on a MSN outside of the range specified in the
service information. To safeguard against this, we included a logbook
check of all airplanes prior to doing any replacements.
We are not changing the final rule AD action based on this comment.
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 the
changes noted above and minor editorial corrections. We have determined
that these changes:
--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 260 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 accomplish the
logbook check:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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1 workhour x $65 per hour = $65..... Not applicable......... $65 $65 x 260 = $16,900.
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We estimate the following costs to accomplish the replacement:
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Parts cost per flap Total cost on U.S.
Labor cost per flap flexshaft flexshaft Total cost per airplane operators
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2 workhours per flap flexshaft (4 Parts covered under $130 x 4 flap Maximum cost for
flap flexshafts per airplane) x $65 warranty by the flexshafts = $520 to replacing all 4 flap
per hour = $130 per flap flexshaft. manufacturer. replace all 4 flap flexshafts on all 260
flexshafts. airplanes = $520 x 260
= $135,200.
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Compliance Time of This AD
What is the compliance time of this AD? The compliance time for the
replacement that will be required by this AD is ``within the next 30
days after the effective date of this AD.''
Why is this compliance time presented in calendar time instead of
hours TIS? The unsafe condition specified by this AD is caused by
corrosion. Corrosion can occur regardless of whether the airplane is in
operation or is in storage. Therefore, to assure that the unsafe
condition specified in this AD does not go undetected for a long period
of time, a compliance time of calendar time is utilized.
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
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. 2004-CE-08-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:
2004-12-11 Pilatus Aircraft Ltd.: Amendment 39-13670; Docket No.
2004-CE-08-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on July 26, 2004.
What Other ADs Are Affected by This Action?
(b) None.
[[Page 33561]]
What Airplanes Are Affected by This AD?
(c) This AD affects Model PC-12 and PC-12/45 airplanes, all
serial numbers, that are:
(1) equipped with an inboard and/or outboard flap flexshaft,
part number (P/N) 945.02.02.203 and/or P/N 945.02.02.204; and
(2) 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
prevent rupture of the flap flexshafts due to corrosion, which could
cause the flap system to become inoperable.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following. If you
already replaced both the inboard and outboard flap flexshafts, P/N
945.02.02.203 and P/N 945.02.02.204, following Pilatus PC12 Service
Bulletin No. 27-015, dated June 4, 2003, then paragraph (e)(5) of
this AD is the only paragraph that applies to you:
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Actions Compliance Procedures
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(1) For affected airplanes Within the next 30 The owner/operator
with a manufacturer serial days after July 26, holding at least a
number (MSN) of 489 or 2004 (the effective private pilot
lower: check the airplane date of this AD). certificate as
logbook to determine if P/N authorized by
945.02.02.203 and P/N section 43.7 of the
945.02.02.204 inboard and Federal Aviation
outboard flap flexshafts Regulations (14 CFR
are installed. 43.7) may perform
this check.
(2) For affected airplanes Within the next 30 The owner/operator
with a MSN of 490 and days after July 26, holding at least a
above: check the airplane 2004 (the effective private pilot
logbook to ensure that P/N date of this AD). certificate as
945.02.02.203 and P/N authorized by
945.02.02.204 inboard and section 43.7 of the
outboard flap flexshafts Federal Aviation
have not been installed Regulations (14 CFR
since delivery. 43.7) may perform
this check.
(3) If you can positively Not Applicable...... Not applicable.
determine that both P/Ns
945.02.02.203 and
945.02.02.204 inboard and
outboard flap flexshafts
are not installed, then no
replacement is required.
(4) If you cannot positively Before further Follow Pilatus PC12
determine that both P/Ns flight after the Service Bulletin
945.02.02.203 and logbook checks No. 27-015 as
945.02.02.204, inboard and required in specified in
outboard flap flexshafts paragraph (e)(1) paragraph (f) of
are not installed, then you and (e)(2) of this this AD.
must replace each one or AD.
both with P/N 945.02.02.205
and P/N 945.02.02.206, as
applicable (or a later FAA-
approved manufactured part
of improved design).
(5) Do not install inboard As of July 26, 2004 Not applicable.
and outboard flap (the effective date
flexshafts, P/Ns of this AD).
945.02.02.203 and
945.02.02.204.
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What Revision Levels Do the Affected Service Bulletin Incorporate?
(f) The service bulletin required to do the actions required in
this AD incorporates the following pages:
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Affected pages Revision level Date
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1 and 2......................... A................. November 13, 2003.
3 through 11.................... Original Issue.... June 4, 2003.
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May I Request an Alternative Method of Compliance?
(g) 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.
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. 27-015, pages 1
and 2, Revision A, dated November 13, 2003, pages 3 through 11,
Original issue, dated June 4, 2003. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You
may get a copy from Pilatus Aircraft Ltd., Customer Liaison Manager,
CH-6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile:
+41 41 619 7311; e-mail: SupportPC12@pilaltus-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. You may review copies at FAA, Central
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas
City, Missouri 64106; or 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Is There Other Information That Relates to This Subject?
(i) Swiss AD Number HB-2004-068, dated March 4, 2004, also
addresses the subject of this AD.
Issued in Kansas City, Missouri, on June 3, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-13334 Filed 6-15-04; 8:45 am]
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