[Federal Register Volume 68, Number 29 (Wednesday, February 12, 2003)]
[Proposed Rules]
[Pages 7081-7084]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-3449]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 68, No. 29 / Wednesday, February 12, 2003 / 
Proposed Rules  

[[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).

-----------------------------------------------------------------------

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: [email protected]. 
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:

----------------------------------------------------------------------------------------------------------------
                                                           Total cost
                Labor cost                   Parts cost   per airplane        Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
7 workhours x $60 per hour = $420.........         $300          $720   $720 x 32 = $23,040.
----------------------------------------------------------------------------------------------------------------

    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:

----------------------------------------------------------------------------------------------------------------
                   Actions                                Compliance                        Procedures
----------------------------------------------------------------------------------------------------------------
(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).
----------------------------------------------

[[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).
----------------------------------------------
(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.
----------------------------------------------
(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.
----------------------------------------------
(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.).
----------------------------------------------
(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.
----------------------------------------------
(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.
----------------------------------------------
(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.
----------------------------------------------
(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.
----------------------------------------------

[[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.
----------------------------------------------------------------------------------------------------------------


    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