[Federal Register: February 12, 2003 (Volume 68, Number 29)]
[Proposed Rules]
[Page 7081-7084]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12fe03-11]
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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.
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[[Page 7081]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-01-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6
airplanes. This proposed AD would require you to inspect and correct,
as necessary, the aileron control bellcrank assemblies at the wing and
fuselage locations. This proposed AD is the result of mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Switzerland. The actions specified by this proposed 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: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before March 21, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-01-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: 9-ACE-7-Docket@faa.gov.
Comments sent electronically must contain ``Docket No. 2003-CE-01-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in Microsoft Word 97 for
Windows or ASCII text.
You may get service information that applies to this proposed 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 also view this information at
the Rules Docket at the address above.
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:
Comments Invited
How do I comment on this proposed AD? The FAA invites comments on
this proposed rule. You may submit whatever written data, views, or
arguments you choose. You need to include the rule's docket number and
submit your comments to the address specified under the caption
ADDRESSES. We will consider all comments received on or before the
closing date. We may amend this proposed rule in light of comments
received. Factual information that supports your ideas and suggestions
is extremely helpful in evaluating the effectiveness of this proposed
AD action and determining whether we need to take additional rulemaking
action.
Are there any specific portions of this proposed AD I should pay
attention to? The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed rule that might suggest a need to modify the proposed rule.
You may view all comments we receive before and after the closing date
of the proposed rule in the Rules Docket. We will file a report in the
Rules Docket that summarizes each contact we have with the public that
concerns the substantive parts of this proposed AD.
How can I be sure FAA receives my comment? If you want FAA to
acknowledge the receipt of your mailed comments, you must include a
self-addressed, stamped postcard. On the postcard, write ``Comments to
Docket No. 2003-CE-01-AD.'' We will date stamp and mail the postcard
back to you.
Discussion
What events have caused this proposed 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.
What are the consequences if the condition is not corrected?
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.
Is there service information that applies to this subject? Pilatus
has issued Service Bulletin No. 27-001, dated June 5, 2002.
What are the provisions of this service information? The service
bulletin includes procedures for:
--Inspecting, before removal, the bellcrank assemblies to identify
which have a circlip installed;
--Removing the bellcrank assemblies;
--Inspecting the bellcrank assemblies for loose or worn bearings;
--Inspecting the control-cable attachment bolts for correct type and
for rub damage;
--Staking and locking the bearing in the housings of the wing
bellcranks; and
--Reinstalling the bellcrank assemblies.
What action did the FOCA take? The FOCA classified this service
bulletin as mandatory and issued Swiss AD Number HB 2002-642, dated
November 15, 2002, in order to ensure the continued airworthiness of
these airplanes in Switzerland.
Was this in accordance with the bilateral airworthiness agreement?
These airplane models are manufactured in Switzerland and are type
certificated for operation in the
[[Page 7082]]
United States under the provisions of Sec. 21.29 of the Federal
Aviation Regulations (14 CFR 21.29) and the applicable bilateral
airworthiness agreement.
Pursuant to this bilateral airworthiness agreement, the FOCA has
kept FAA informed of the situation described above.
The FAA's Determination and an Explanation of the Provisions of this
Proposed AD
What has FAA decided? The FAA has examined the findings of the
FOCA; reviewed all available information, including the service
information referenced above; and determined that:
--The unsafe condition referenced in this document exists or could
develop on other Pilatus Model PC-6 airplanes of the same type design
that are on the U.S. registry;
--The actions specified in the previously-referenced service
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.
What would this proposed AD require? This proposed AD would require
you to incorporate the actions in the previously-referenced service
bulletin.
Cost Impact
How many airplanes would this proposed AD impact? We estimate that
this proposed AD affects 32 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
accomplish the proposed 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 proposed
inspections. We have no way of determining the number of airplanes that
may need such repair.
Regulatory Impact
Would this proposed AD impact various entities? The regulations
proposed herein 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. Therefore, it is determined that this
proposed rule would not have federalism implications under Executive
Order 13132.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this proposed
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) if
promulgated, 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 draft regulatory
evaluation prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. FAA amends Sec. 39.13 by adding a new airworthiness directive
(AD) to read as follows:
Pilatus Aircraft, Ltd.: 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, the wing Within the next 100 hours time- In accordance with Pilatus
bellcrank assemblies, part numbers (P/N) in-service (TIS) after the Aircraft Ltd. PC-6 Service
6132.0071.51 and 6132.0071.52, for installed effective date of this AD, Bulletin No. 27-001, dated
circlips, P/N N237. unless already accomplished. June 5, 2002, and the
(i) If circlips are installed, perform the applicable maintenance manual.
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).
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[[Page 7083]]
(2) Inspect, before removal, the fuselage Prior to further flight after In accordance with Pilatus
bellcrank assembly, P/N 6232.0118.00, for the inspection required in Aircraft Ltd. PC-6 Service
the circlip installed on the housing to paragraph (d)(1) of this AD. Bulletin No. 27-001, dated
prevent axial movement of the bellcrank on June 5, 2002, and the
its bearing and the flange of the housing to applicable maintenance manual.
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).
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(3) Remove the wing bellcrank assemblies, P/ Prior to further flight after In accordance with Pilatus
Ns 6132.0071.51 and 6132.0071.52, and the inspections required in Aircraft Ltd. PC-6 Service
inspect for worn or damaged bearings. paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
Replace worn or damaged bearings. this AD, as applicable. June 5, 2002, and the
applicable maintenance manual.
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(4) Stake and lock the bearing in the housing Prior to further flight after In accordance with Pilatus
of the wing bellcranks, P/Ns 6132.0071.51 the inspections required in Aircraft Ltd. PC-6 Service
and 6132.0071.52. paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
this AD, as applicable. June 5, 2002, and the
applicable maintenance manual.
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(5) Inspect the wing bellcranks control-cable Prior to further flight after In accordance with Pilatus
attachment bolts for correct type and for the inspections required in Aircraft Ltd. PC-6 Service
signs of rub damage on the heads. Replace paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
bolts which are damaged and/or have a total this AD. June 5, 2002, and the
length (including head) of more than 21.5 mm applicable maintenance manual.
(0.85 in.).
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(6) Inspect the wing bellcranks support plate
for signs of rub damage caused by the bolts.
If damage is 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. Prior to further flight after In accordance with Pilatus
the inspections required in Aircraft Ltd. PC-6 Service
paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
this AD. June 5, 2002, and the
applicable maintenance manual.
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(7) Reinstall wing bellcrank assemblies. Prior to further flight after In accordance with Pilatus
the inspections required in Aircraft Ltd. PC-6 Service
paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
this AD. June 5, 2002, and the
applicable maintenance manual.
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(8) Remove the fuselage bellcrank assembly, P/
N 6232.0118.00, and inspect the housing for
wear, damage, and signs of axial movement of
the bearing in the housing. Replace worn or
damaged bearings. If any 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. Prior to further flight after In accordance with Pilatus
the inspections required in Aircraft Ltd. PC-6 Service
paragraphs (d)(1) and (d)(2) of Bulletin No. 27-001, dated
this AD. June 5, 2002, and the
applicable maintenance manual.
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(9) Reinstall the fuselage bellcrank Prior to further flight after In accordance with Pilatus
assembly. Ensure that the fuselage bellcrank the inspections required in Aircraft Ltd. PC-6 Service
assembly is installed so that the surface of paragraphs (d)(1), (d)(2) and Bulletin No. 27-001, dated
the bellcrank with the flange of the housing (d)(8) of this AD. June 5, 2002, and the
is installed to the rear. The effect of this applicable maintenance manual.
is to lock the bellcrank on the bearing tube
and thus prevent movement.
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[[Page 7084]]
(10) Do not install any bellcrank assemblies, As of the effective date of this In accordance with Pilatus
P/Ns 6132.0071.51, 6132.0071.52, and AD. Aircraft Ltd. PC-6 Service
6232.0118.00 (or FAA-approved equivalent Bulletin No. 27-001, dated
part numbers), unless the aileron assembly June 5, 2002, and the
has been inspected, modified, and installed. applicable maintenance manual.
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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) How do I get copies of the documents referenced in this AD?
You may get copies of the documents 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
these documents at FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
Note 4: The subject of this AD is addressed in Swiss AD Number
HB 2002-642, dated November 15, 2002.
Issued in Kansas City, Missouri, on February 4, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-3449 Filed 2-11-03; 8:45 am]
BILLING CODE 4910-13-P