[Federal Register Volume 67, Number 212 (Friday, November 1, 2002)]
[Rules and Regulations]
[Pages 66541-66544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-27418]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-28-AD; Amendment 39-12927; AD 2002-22-03]
RIN 2120-AA64


Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 
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 certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7 
airplanes. This AD requires you to repetitively inspect the main 
landing gear front attachment brackets for cracks, and, if cracks are 
found, install improved-design brackets. Installing the improved-design 
brackets terminates the required inspections. 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 cracks in the main landing gear 
front attachment brackets,

[[Page 66542]]

which could result in failure of the brackets. Such failure could lead 
to the main landing gear leg detaching from the wing main spar.

DATES: This AD becomes effective on December 20, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
December 20, 2002.

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. 2002-CE-28-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 certain Pilatus Model PC-7 airplanes. The 
FOCA reports that an operator of a similar aircraft type design, which 
uses identical main landing gear support brackets, reported a single 
crack in one bracket. A fleet inspection of the operator's aircraft 
revealed stress corrosion cracking in more than 20 aircraft.

What Is the Potential Impact if FAA Took No Action?

    Cracks in the main landing gear front attachment brackets could 
result in failure of the brackets. Such failure could lead to the main 
landing gear leg detaching from the wing main spar.

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-7 airplanes. This proposal was published in 
the Federal Register as a notice of proposed rulemaking (NPRM) on 
August 9, 2002 (67 FR 51794). The NPRM proposed to repetitively inspect 
the main landing gear front attachment brackets for cracks, and, if 
cracks are found, install improved-design brackets. Installing the 
improved-design brackets terminates the required inspections.

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?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:
--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 14 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 inspection:

----------------------------------------------------------------------------------------------------------------
                                                               Total cost per
             Labor cost                     Parts cost            airplane        Total cost on  U.S. operator
----------------------------------------------------------------------------------------------------------------
4 workhours x $60 = $240............  No parts required.....            $240   $240 x 14 = $3,360.
----------------------------------------------------------------------------------------------------------------

    The FAA has no method of determining the number of repetitive 
inspections each owner/operator would incur over the life of each of 
the affected airplanes so the cost impact is based on the initial 
inspection.
    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

------------------------------------------------------------------------
                                                       Total cost per
          Labor cost                Parts cost            airplane
------------------------------------------------------------------------
80 workhours x $60 = $4,800     $2,500 per side..  $4,800 + $2,500 =
 per side.                                          $7,300 per side.
------------------------------------------------------------------------

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

[[Page 66543]]

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

    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

    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 AD to read as follows:

2002-22-03 Pilatus Aircraft LTD.: Amendment 39-12927; Docket No. 
2002-CE-28-AD.

    (a) What airplanes are affected by this AD? This AD affects 
Model PC-7 airplanes, serial numbers 101 through 618, 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 cracks in the main 
landing gear front attachment brackets, which could result in 
failure of the brackets. Such failure could lead to the main landing 
gear leg detaching from the wing main spar.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
         Compliance                  Actions             Procedures
------------------------------------------------------------------------
(1) Initial Inspection: At    Inspect, using the    In accordance with
 whichever of the following    Impedance-Plane       the ACCOMPLISHMENT
 occurs later, unless          Eddy-Current          INSTRUCTIONS
 already accomplished: (i)     Inspection, both      section of Pilatus
 Upon the accumulation of      main landing gear     PC-7 Service
 3,000 hours time-in-service   front attachment      Bulletin No. 57-
 (TIS) on the attachment       brackets, part        004, Revision No.
 brackets or 10 years after    number (P/N)          1, dated June 17,
 installation of the           111.34.07.105 and P/  2002; the
 brackets, whichever occurs    N 111.34.07.106 for   ACCOMPLISHMENT
 first; or (ii) within 90      cracks.               INSTRUCTIONS
 days after December 20,                             section of Pilatus
 2002 (the effective date of                         PC-7 Service
 this AD).                                           Bulletin No. 57-
                                                     005, dated
                                                     September 10, 2001;
                                                     and Pilatus PC-7
                                                     Maintenance Manual,
                                                     Temporary Revision
                                                     No. 05-10, dated
                                                     September 10, 2001.
-----------------------------
(2) Repetitive Inspections:   Inspection, using     In accordance with
 Within 12 calendar months     the Impedance-Plane   the ACCOMPLISHMENT
 after the initial             Eddy-Current          INSTRUCTIONS
 inspection required in        Inspection, both      section of Pilatus
 paragraph (d)(1) of this AD   main landing gear     PC-7 Service
 and thereafter at intervals   front attachment      Bulletin No. 57-
 not to exceed 12 calendar     brackets, P/N         004, Revision No.
 months.                       111.34.07.105 and P/  1, dated June 17,
                               N 111.34.07.106 for   2002; the
                               cracks.               ACCOMPLISHMENT
                                                     INSTRUCTIONS
                                                     section of Pilatus
                                                     PC-7 Service
                                                     Bulletin No. 57-
                                                     005, dated
                                                     September 10, 2001;
                                                     and Pilatus PC-7
                                                     Maintenance Manual,
                                                     Temporary Revision
                                                     No. 05-10, dated
                                                     September 10, 2001.
-----------------------------
(3) Prior to further flight   If a crack is found   In accordance with
 after the inspection in       in any main landing   the ACCOMPLISHMENT
 which the damage was found.   gear front            INSTRUCTIONS
                               attachment bracket    section of Pilatus
                               during any            PC-7 Service
                               inspection required   Bulletin No. 57-
                               in this AD, replace   005, dated
                               with an improved      September 10, 2001.
                               bracket, P/N
                               557.10.09.045, P/N
                               557.10.09.046, or
                               FAA-approved
                               equivalent P/N.
                               Repetitive
                               inspections are
                               still required on
                               any P/N
                               111.34.07.105 and P/
                               N 111.34.07.106 for
                               cracks.
-----------------------------
(4) At any time as            You may terminate     In accordance with
 terminating action for the    the inspections       the ACCOMPLISHMENT
 repetitive inspections.       required in           INSTRUCTIONS
 However, you must replace     paragraphs (d)(1)     section of Pilatus
 prior to further flight if    and (d)(2) of this    PC-7 Service
 you find cracks during any    AD when improved      Bulletin No. 57-
 inspections required by       design main landing   005, dated
 this AD.                      gear front            September 10, 2001.
                               attachment
                               brackets, P/N
                               557.10.09.045, P/N
                               557.10.09.046, or
                               FAA-approved
                               equivalent P/Ns,
                               are installed on
                               both sides of the
                               airplane.
-----------------------------
(5) As of December 20, 2002   Only install main     Not Applicable.
 (the effective date of this   landing gear
 AD).                          brackets that are P/
                               N 557.10.09.045, P/
                               N 557.10.09.046, or
                               FAA-approved
                               equivalent P/Ns.
------------------------------------------------------------------------


    Note 1: If you find cracks on one side only, you are only 
required to replace the damaged side with the new improved-design 
bracket and continue the repetitive inspections required by 
paragraph (d)(2) of this AD. Repetitive inspections are still 
required on any installed bracket with either P/N 111.34.07.105 or 
P/N 111.34.07.106.

    (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 2: 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

[[Page 66544]]

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 PC-7 Service Bulletin No. 57-004, Revision No. 1, dated 
June 17, 2002; Pilatus PC-7 Service Bulletin No. 57-005, dated 
September 10, 2001; and Pilatus PC-7 Maintenance Manual, Temporary 
Revision No. 05-10, dated September 10, 2001. 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 3: The subject of this AD is addressed in Swiss AD HB 2002-
270, dated June 24, 2002.

    (i) When does this amendment become effective ? This amendment 
becomes effective on December 20, 2002.


    Issued in Kansas City, Missouri, on October 22, 2002.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-27418 Filed 10-31-02; 8:45 am]
BILLING CODE 4910-13-P