[Federal Register Volume 67, Number 7 (Thursday, January 10, 2002)]
[Rules and Regulations]
[Pages 1286-1287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-149]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-30-AD; Amendment 39-12579; AD 2001-26-13]
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 inspect the landing-gear emergency-
extension cable for damage and replace if necessary; verify the correct 
installation of the bowden-cable conduit clamp and correct if 
necessary; and modify the temperature-control lever mechanism. 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 the malfunction of the 
emergency landing-gear extension system. Insufficient clearance between 
the temperature-control lever mechanism and the landing-gear emergency-
extension cable could result in damage to the emergency landing gear 
extension cable, or the cable could get caught on the temperature 
control lever. Damage to, or interference with, the landing-gear 
emergency-extension cable could lead to a malfunction of the emergency 
landing-gear extension system.

DATES: This AD becomes effective on February 12, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
February 12, 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 6509; facsimile: +41 41 610 3351. 
You may view this information at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 2001-CE-30-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 one occurrence of restricted movement of the temperature 
control lever. Investigation of the problem revealed that the landing-
gear emergency-extension cable was caught on the temperature-control 
lever mechanism. Insufficient clearance between the landing-gear 
emergency-extension cable and the temperature-control lever caused the 
interference. This interference could also cause damage to the landing-
gear emergency-extension cable.

What Is the Potential Impact if FAA Took No Action?

    If not detected and corrected, damage to or interference with the 
landing-gear emergency-extension cable could lead to a malfunction of 
the emergency landing-gear extension system.

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 
October 10, 2001 (66 FR 51611). The NPRM proposed to require you to 
inspect the landing-gear emergency-extension cable for damage; replace 
any damaged landing-gear emergency-extension cable; verify the correct 
installation of the bowden-cable conduit clamp; correct improper 
installation of the clamp; and install a new bolt and a new nut on the 
temperature-control lever mechanism.

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 13 airplanes in the U.S. registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    The manufacturer has agreed to pay the costs for the inspection, 
replacement parts, and installation workhours.
    The only impact this AD will have on the owners/operators of the 
affected airplanes is the time it will take to have the actions of this 
AD incorporated.

Compliance Time of This AD

What Will Be the Compliance Time of This AD?

    The compliance time of this AD is ``within the next 12 calendar 
months after the effective date of this AD.''

Why Is the Compliance Time Presented in Calendar Time Instead of Hours 
Time-in-Service (TIS)?

    Although malfunction of the emergency landing gear extension system 
is unsafe during flight, the condition is not a direct result of 
airplane operation. The chance of this situation occurring is the same 
for an airplane with 10 hours TIS as it would be for an airplane with 
500 hours TIS.

[[Page 1287]]

A calendar time for compliance will ensure that the unsafe condition is 
addressed on all airplanes in a reasonable time period.

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 adding a new AD to read as follows:

2001-26-13  Pilatus Aircraft Ltd.: Amendment 39-12579; Docket No. 
2001-CE-30-AD.

    (a) What airplanes are affected by this AD? This AD affects 
Model PC-7 airplanes, Manufacturer Serial Number (MSN) 001 through 
MSN 616, 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 the malfunction of the emergency 
landing-gear extension system. Insufficient clearance between the 
temperature-control lever mechanism and the landing-gear emergency-
extension cable could result in damage to the emergency landing gear 
extension cable, or the cable could get caught on the temperature 
control lever. Damage to, or interference with, the landing-gear 
emergency-extension cable could lead to a malfunction of the 
emergency landing-gear extension system.
    (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 the landing-gear      Inspect within the  In accordance with
 emergency-extension cable for     next 12 calendar    Pilatus PC-7
 damage and replace any damaged    months after        Service Bulletin
 cable found.                      February 12, 2002   No. 32-020, dated
                                   (the effective      July 5, 2001.
                                   date of this AD).
                                   Replace prior to
                                   further flight.
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(2) Verify the correct            Prior to further    In accordance with
 installation of the bowden-       flight after the    Pilatus PC-7
 cable conduit clamp, correct if   inspection          Service Bulletin
 necessary, and install a new      required in         No. 32-020, dated
 bolt and a new nut in the         paragraph (d)(1)    July 5, 2001.
 temperature-control lever         of this AD.
 mechanism.
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(3) Do not install any            As of February 12,  Not applicable.
 temperature-control lever         2002 (the
 mechanism (or FAA-approved        effective date of
 equivalent part number), unless   this AD).
 it has been modified as
 required in paragraph (d)(2) of
 this AD.
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    (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 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.

    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 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 
sections 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. 32-020, dated July 5, 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 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.

    Note 2: The subject of this AD is addressed in Swiss AD HB 2001-
483, dated August 20, 2001.

    (i) When does this amendment become effective? This amendment 
becomes effective on February 12, 2002.

    Issued in Kansas City, Missouri, on December 21, 2001.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-149 Filed 1-9-02; 8:45 am]
BILLING CODE 4910-13-U