[Federal Register Volume 66, Number 196 (Wednesday, October 10, 2001)]
[Proposed Rules]
[Pages 51611-51613]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-25398]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-30-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Pilatus Aircraft Ltd. (Pilatus) Model 
PC-7 airplanes. This proposed AD would require 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 proposed AD is the result of mandatory continuing 
airworthiness information (MCAI)

[[Page 51612]]

issued by the airworthiness authority for Switzerland. The actions 
specified by this proposed 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: The Federal Aviation Administration (FAA) must receive any 
comments on this proposed rule on or before December 4, 2001.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-30-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 get service information that applies to this proposed AD 
from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6509; facsimile: +41 41 610 3351. 
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 rule. You may 
view all comments we receive before and after the closing date of the 
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 comments, you must include a self-
addressed, stamped postcard. On the postcard, write ``Comments to 
Docket No. 2001-CE-30-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 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 are the consequences if the condition is not corrected?
    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.
    Is there service information that applies to this subject? Pilatus 
has issued Service Bulletin No. 32-020, dated July 5, 2001.
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Inspecting the landing-gear emergency-extension cable for damage;
--Replacing any damaged landing-gear emergency-extension cable;
--Verifying the correct installation of the bowden-cable conduit clamp;
--Correcting improper installation of the clamp; and
--Installing a new bolt and a new nut on the temperature-control lever 
mechanism.

    What action did the FOCA take? The FOCA classified this service 
bulletin as mandatory and issued Swiss AD Number HB 2001-483, dated 
August 20, 2001, in order to ensure the continued airworthiness of 
these airplanes in Switzerland.
    Was this in accordance with the bilateral airworthiness agreement? 
This airplane model is manufactured in Switzerland and is type 
certificated for operation in the United States under the provisions of 
section 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 PC-7 airplanes of the same type design;
--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 13 airplanes in the U.S. registry.
    What would be the cost impact of this proposed 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 proposed AD would have on the owners/operators 
of the affected airplanes is the time it would take to have the actions 
of this proposed AD incorporated.

Compliance Time of This Proposed AD

    What would be the compliance time of this proposed AD? The 
compliance time of this proposed 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

[[Page 51613]]

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

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. 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:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
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(1) Inspect the landing-gear  Inspect within the    In
 emergency-extension cable     next 12 calendar      accordance with
 for damage and replace any    months after the      Pilatus Service
 damaged cable found.          effective date of     Bulletin No. 32-
                               this AD. Replace      020, dated July 5,
                               prior to further      2001.
                               flight
(2) Verify the correct        Prior to   In
 installation of the bowden-   further flight        accordance with
 cable conduit clamp,          after the             Pilatus Service
 correct if necessary, and     inspection required   Bulletin No. 32-
 install a new bolt and a      in paragraph (d)(1)   020, dated July 5,
 new nut in the temperature-   of this AD            2001.
 control lever mechanism.
(3) Do not install any        As of the  Not
 temperature-control lever     effective date of     applicable.
 mechanism (or FAA-approved    this AD
 equivalent part number),
 unless it has been modified
 as required in paragraph
 (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) 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 6509; facsimile: +41 41 610 3351. 
You may view these documents at FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

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


    Issued in Kansas City, Missouri, on October 2, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-25398 Filed 10-9-01; 8:45 am]
BILLING CODE 4910-13-U