[Federal Register: April 29, 2003 (Volume 68, Number 82)]
[Rules and Regulations]
[Page 22582-22584]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29ap03-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-01-AD; Amendment 39-13130; AD 2003-09-01]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes.
This AD requires you to inspect and correct, as necessary, the aileron
control bellcrank assemblies at the wing and fuselage locations. This
AD is the result of mandatory continuing airworthiness information
(MCAI) issued by the airworthiness authority for Switzerland. The
actions specified by this AD are intended to detect and correct
increased friction in the aileron control bellcrank assemblies, which
could result in failure of the aileron flight-control system. Such
failure could lead to problems in controlling flight.
DATES: This AD becomes effective on June 17, 2003.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of June
17, 2003.
ADDRESSES: You may get the service information referenced in this AD
from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224;
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 this information at the
Federal Aviation Administration (FAA), Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-01-AD, 901
Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the
Federal Register, 800 North Capitol Street, NW., Suite 700, Washington,
DC.
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 all Pilatus
Model PC-6 airplanes. The FOCA reports one occurrence where the pilot
reported increased friction on the ailerons. Inspection revealed
unwanted axial movement of the aileron bellcrank assemblies, part
numbers 6132.0071.51, 6132.0071.52, and 6232.0118.00. The axial
movement is caused by deterioration of the adhesive bond around the
bellcrank bearings which could cause the heads of the control cable
attachment bolts to catch on the adjacent structure.
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 Model PC-6 airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on February 12, 2003 (68 FR 7081). The NPRM
proposed to you to inspect and correct, as necessary, the aileron
control bellcrank assemblies at the wing and fuselage locations.
What is the potential impact if FAA took no action? Increased
friction in the aileron control bellcrank assemblies could result in
failure of the aileron flight-control system. Such failure could lead
to problems in controlling flight.
Was the public invited to comment? The FAA encouraged interested
persons to participate in the making of this amendment. We did not
receive any comments on the proposed rule or on our determination of
the cost to the public.
FAA's Determination
What is FAA's final determination on this issue? We carefully
reviewed all available information related to the subject presented
above and determined that air safety and the public interest require
the adoption of the rule as proposed except for the changes discussed
above and minor editorial questions. We have determined that these
changes and minor corrections:
[[Page 22583]]
--Provide 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.
Cost Impact
How many airplanes does this AD impact? We estimate that this AD
affects 32 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
inspections and modifications:
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Total cost
Labor cost Parts cost per airplane Total cost on U.S. operators
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7 workhours x $60 per hour = $420...... $300 $720 $720 x 32 = $23,040.
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We have no way of estimating costs to accomplish any necessary
repairs that would be required based on the results of the inspections.
We have no way of determining the number of airplanes that may need
such repair.
Regulatory Impact
Does this AD impact various entities? The regulations adopted
herein 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. Therefore, it is determined that this final rule does not
have federalism implications under Executive Order 13132.
Does this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this action (1) is not a
``significant regulatory action'' under Executive Order 12866; (2) is
not a ``significant rule'' under 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. A copy
of the final evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
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:
2003-09-01 Pilatus Aircraft Ltd.: Amendment 39-13130; Docket No.
2003-CE-01-AD.
(a) What airplanes are affected by this AD? This AD affects
Model PC-6 airplanes, all manufacturer serial numbers (MSN) up to
and including 939, that are certificated in any category.
(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraph (a) of this AD must
comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to detect and correct increased friction in the
aileron control bellcrank assemblies, which could result in failure
of the aileron flight-control system. Such failure could lead to
problems in controlling flight.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Inspect, before removal, Within the next 100 In accordance with
the wing bellcrank hours time-in- Pilatus Aircraft
assemblies, part numbers (P/ service (TIS) after Ltd. PC-6 Service
N) 6132.0071.51 and June 17, 2003 (the Bulletin No. 27-
6132.0071.52, for installed effective date of 001, dated June 5,
circlips, P/N N237. this AD), unless 2002, and the
already applicable
accomplished. maintenance manual.
(i) If circlips are
installed, perform the
actions required in
paragraphs (d)(5) and
(d)(6).
(ii) If circlips are not
installed, perform all
actions required by
paragraphs (d)(3), (d)(4),
(d)(5), (d)(6), and (d)(7).
(2) Inspect, before removal, Prior to further In accordance with
the fuselage bellcrank flight after the Pilatus Aircraft
assembly, P/N 6232.0118.00, inspection required Ltd. PC-6 Service
for the circlip installed in paragraph (d)(1) Bulletin No. 27-
on the housing to prevent of this AD. 001, dated June 5,
axial movement of the 2002, and the
bellcrank on its bearing applicable
and the flange of the maintenance manual.
housing to the rear. If the
fuselage bellcrank assembly
has either no circlip and/
or is not installed as
required, perform the
actions in paragraphs
(d)(8) and (d)(9).
(3) Remove the wing Prior to further In accordance with
bellcrank assemblies, P/Ns flight after the Pilatus Aircraft
6132.0071.51 and inspections Ltd. PC-6 Service
6132.0071.52, and inspect required in Bulletin No. 27-
for worn or damaged paragraphs (d)(1) 001, dated June 5,
bearings. Replace worn or and (d)(2) of this 2002, and the
damaged bearings. AD, as applicable. applicable
maintenance manual.
(4) Stake and lock the Prior to further In accordance with
bearing in the housing of flight after the Pilatus Aircraft
the wing bellcranks, P/Ns inspections Ltd. PC-6 Service
6132.0071.51 and required in Bulletin No. 27-
6132.0071.52. paragraphs (d)(1) 001, dated June 5,
and (d)(2) of this 2002, and the
AD, as applicable. applicable
maintenance manual.
[[Page 22584]]
(5) Inspect the wing Prior to further In accordance with
bellcranks control-cable flight after the Pilatus Aircraft
attachment bolts for inspections Ltd. PC-6 Service
correct type and for signs required in Bulletin No. 27-
of rub damage on the heads. paragraphs (d)(1) 001, dated June 5,
Replace bolts which are and (d)(2) of this 2002, and the
damaged and/or have a total AD. applicable
length (including head) of maintenance manual.
more than 21.5 mm (0.85
in.).
(6) Inspect the wing Prior to further In accordance with
bellcranks support plate flight after the Pilatus Aircraft
for signs of rub damage inspections Ltd. PC-6 Service
caused by the bolts. If required in Bulletin No. 27-
damage is found:. paragraphs (d)(1) 001, dated June 5,
and (d)(2) of this 2002, and the
AD. applicable
maintenance manual.
(i) Obtain a repair scheme
from the manufacturer
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme.
(7) Reinstall wing bellcrank Prior to further In accordance with
assemblies. flight after the Pilatus Aircraft
inspections Ltd. PC-6 Service
required in Bulletin No. 27-
paragraphs (d)(1) 001, dated June 5,
and (d)(2) of this 2002, and the
AD. applicable
maintenance manual.
(8) Remove the fuselage Prior to further In accordance with
bellcrank assembly, P/N flight after the Pilatus Aircraft
6232.0118.00, and inspect inspections Ltd. PC-6 Service
the housing for wear, required in Bulletin No. 27-
damage, and signs of axial paragraphs (d)(1) 001, dated June 5,
movement of the bearing in and (d)(2) of this 2002, and the
the housing. Replace worn AD. applicable
or damaged bearings. If any maintenance manual.
signs of axial movement of
a bearing are found:
(i) Obtain a repair scheme
from the manufacturer
through FAA at the address
specified in paragraph (f)
of this AD.
(ii) Incorporate this repair
scheme.
(9) Reinstall the fuselage Prior to further In accordance with
bellcrank assembly. Ensure flight after the Pilatus Aircraft
that the fuselage bellcrank inspections Ltd. PC-6 Service
assembly is installed so required in Bulletin No. 27-
that the surface of the paragraphs (d)(1), 001, dated June 5,
bellcrank with the flange (d)(2) and d)(8) of 2002, and the
of the housing is installed this AD. applicable
to the rear. The effect of maintenance manual.
this is to lock the
bellcrank on the bearing
tube and thus prevent
movement.
(10) Do not install any As of June 17, 2003 In accordance with
bellcrank assemblies, P/Ns (the effective date Pilatus Aircraft
6132.0071.51, 6132,0071.52, of this AD). Ltd. PC-6 Service
and 6232.0118.00 (or FAA- Bulletin No. 27-
approved equivalent part 001, dated June 5,
numbers), unless the 2002, and the
aileron assembly has been applicable
inspected, modified, and maintenance manual.
installed.
------------------------------------------------------------------------
Note 1: Axial movement of serviceable bearings in the housings
of the wing bellcranks is permitted provided no wear or damage to
the bearing is found.
Note 2: Any signs of axial movement of a bearing in the housing
of the fuselage bellcrank assembly requires that you obtain a repair
scheme from the manufacturer through FAA at the address specified in
paragraph (f) of this AD and incorporate the repair scheme.
(e) Can I comply with this AD in any other way? You may use an
alternative method of compliance or adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent
level of safety; and
(2) The Standards Office Manager, Small Airplane Directorate,
approves your alternative. Submit your request through an FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Standards Office Manager.
Note 3: This AD applies to each airplane identified in paragraph
(a) of this AD, regardless of whether it has been modified, altered,
or repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if you have not eliminated the unsafe condition, specific
actions you propose to address it.
(f) Where can I get information about 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.
(g) What if I need to fly the airplane to another location to
comply with this AD? The FAA can issue a special flight permit under
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate your airplane to a location where
you can accomplish the requirements of this AD.
(h) Are any service bulletins incorporated into this AD by
reference? Actions required by this AD must be done in accordance
with Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-001, dated
June 5, 2002. The Director of the Federal Register approved this
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51.
You may get copies from Pilatus Aircraft Ltd., Customer Liaison
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19;
facsimile: +41 41 619 6224; 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 copies at the FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
Note 4: The subject of this AD is addressed in Swiss AD Number
HB 2002-642, dated November 15, 2002.
(i) When does this amendment become effective? This amendment
becomes effective on June 17, 2003.
Issued in Kansas City, Missouri, on April 18, 2003.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-10237 Filed 4-28-03; 8:45 am]
BILLING CODE 4910-13-P