[Federal Register Volume 68, Number 82 (Tuesday, April 29, 2003)]
[Rules and Regulations]
[Pages 22582-22584]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-10237]


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

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.

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

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:

----------------------------------------------------------------------------------------------------------------
                                                        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 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:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(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