Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7 Airplanes

[Federal Register Volume 66, Number 48 (Monday, March 12, 2001)]
[Rules and Regulations]
[Pages 14306-14308]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-5275]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-46-AD; Amendment 39-12138; AD 2001-05-02]
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 supersedes Airworthiness Directive (AD) 98-08-
22, which currently requires inspecting the elevator and rudder 
attachment brackets for cracks and corrosion on certain Pilatus 
Aircraft Ltd. (Pilatus) Model PC-7 airplanes and replacing any cracked 
or corrosion-damaged parts. Since the issuance of AD 98-08-22, Pilatus 
has redesigned the brackets. Installation of these brackets should 
inhibit corrosion, which resulted in cracks or corrosion damage. This 
AD requires you to replace the elevator and rudder attachment brackets 
with parts of improved design. 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 prevent failure of the elevator and rudder attachment 
brackets because of cracks or corrosion damage. Such failure could 
result in the elevator or rudder separating from the airplane with 
consequent loss of airplane control.

DATES: This AD becomes effective on April 27, 2001.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of April 
27, 2001.

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 6509; facsimile: +41 41 610 3351. 
You may examine this information at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 2000-CE-46-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: Roman Gabrys, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4141; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:   

Discussion

    Has FAA taken any action to this point? Reports received from the 
Federal Office for Civil Aviation (FOCA), which is the airworthiness 
authority for Switzerland, revealed instances of corrosion and cracking 
in the elevator and rudder attachment brackets on Pilatus Model PC-7 
airplanes that have been operated in areas of high humidity or salt 
content. This caused FAA to issue AD 98-08-22, Amendment 39-10471 (63 
FR 19175, April 17, 1998). That AD requires you to inspect the elevator 
and rudder attachment brackets for cracks and/or corrosion, and replace 
any cracked or corrosion-damaged parts, as applicable.
    What has happened since AD 98-08-22 to initiate this action? The 
FOCA recently notified FAA of the need to change AD 98-08-22. The FOCA 
reports that Pilatus has redesigned the elevator and rudder attachment 
brackets. Installation of these brackets should inhibit the cause of 
corrosion, which resulted in cracks or corrosion damage.
    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 January 2, 2001 (66 FR 57). The NPRM 
proposed to supersede AD 98-08-22. AD 98-08-22 currently requires 
inspecting the elevator and rudder attachment brackets for cracks and 
corrosion, and replacing any cracked or corrosion-damaged parts. Since 
the issuance of AD 98-08-22, Pilatus has redesigned the brackets. 
Installation of these brackets should inhibit corrosion, which resulted 
in cracks or corrosion damage. The NPRM also proposed to require you to 
replace the elevator and rudder attachment brackets with parts of 
improved design.
    Was the public invited to comment? Interested persons were afforded 
an opportunity to participate in the making of this amendment. No 
comments were received on the proposed rule or the FAA's 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 determined that these minor corrections:

--Will not change the meaning of the AD; and
--Will not add any additional burden upon the public than was already 
proposed.

Cost Impact

    How many airplanes does this AD impact? We estimate that this AD 
affects 8 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 
modification:

[[Page 14307]]



----------------------------------------------------------------------------------------------------------------
                                                                  Total cost per
             Labor cost                      Parts cost              airplane      Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
8 workhours  x  $60 per hour = $480  Parts will be provided by             $480   $480  x  8 = $3,840
                                      the manufacturer free of
                                      charge.
----------------------------------------------------------------------------------------------------------------

    Why is the compliance in hours time-in-service (TIS) and calendar 
time? The affected airplanes are used in general aviation operations. 
Some operators may accumulate 100 hours TIS on the airplane in less 
than 6 months. We have determined that the dual compliance time:

--Gives all owners/operators of the affected airplanes adequate time to 
schedule and do the actions in this AD; and
--Ensures that the unsafe condition referenced in this AD will be 
corrected within a reasonable time period without inadvertently 
grounding any of the affected airplanes.

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

    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 removing Airworthiness Directive (AD) 
98-08-22, Amendment 39-10471 (63 FR 19175, April 17, 1998), and by 
adding a new AD to read as follows:

2001-05-02  Pilatus Aircraft LTD: Amendment 39-12138; Docket No. 
2000-CE-46-AD; Supersedes AD 98-08-22, Amendment 39-10471.

    (a) What airplanes are affected by this AD? This AD affects 
Model PC-7 airplanes, serial numbers MSN 001 through MSN 612, that 
are certificated in any category.
    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent failure of the elevator and rudder 
attachment brackets because of cracks or corrosion damage, which 
could result in the elevator or rudder separating from the airplane 
with consequent loss of airplane control.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Replace the horizontal    Within the next 100   In accordance with
 stabilizer brackets with      hours time-in-        the Accomplishment
 new parts using replacement   service (TIS) or 6    Instructions of
 kit No. 500.50.07.132 and     months after April    Pilatus Service
 replace the vertical          27, 2001 (the         Bulletin No. 55-
 stabilizer bracket with new   effective date of     005, dated March
 parts using replacement kit   this AD), whichever   23, 2000, the
 No. 500.50.07.133.            occurs first,         aircraft
                               unless already        maintenance
                               accomplished.         manuals, and
                                                     illustrated parts
                                                     catalogs.
------------------------------------------------------------------------
(2) Do not install any parts  As of April 27, 2001  Not Applicable.
 identified as old parts in    (the effective date
 replacement kit No.           of this AD).
 500.50.07.132 (or FAA-
 approved equivalent part
 numbers) or 500.50.07.133
 (or FAA-approved equivalent
 part number).
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way?
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The 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 
Manager, Small Airplane Directorate.
    (2) Alternative methods of compliance approved under AD 98-08-
22, which is superseded by this AD, are not approved as alternative 
methods of compliance with this AD.

    Note 1: 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 Roman Gabrys, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4141; 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 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and

[[Page 14308]]

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 Service Bulletin No. 55-005, dated March 23, 2000. The 
Director of the Federal Register approved this incorporation by 
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get 
copies from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 
Stans, Switzerland. You can look at 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.
    (i) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 98-08-22, Amendment 39-10471.
    (j) When does this amendment become effective? This amendment 
becomes effective on April 27, 2001.

    Note 2: The subject of this AD is addressed in Swiss AD HB 2000-
411, dated September 27, 2000.


    Issued in Kansas City, Missouri, on February 26, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-5275 Filed 3-9-01; 8:45 am]
BILLING CODE 4910-13-P

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