[Federal Register Volume 66, Number 206 (Wednesday, October 24, 2001)]
[Proposed Rules]
[Pages 53738-53741]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-26587]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 66, No. 206 / Wednesday, October 24, 2001 / 
Proposed Rules  

[[Page 53738]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-33-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-7, PC-
12, and PC-12/45 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to all Pilatus Aircraft Ltd. Models PC-7, PC-12, 
and PC-12/45 airplanes that incorporate a certain engine-driven pump. 
This proposed AD would require you to: inspect the joints between the 
engine-driven pump housing, relief valve housing, and the relief-valve 
cover for signs of fuel leakage or extruding gasket material; replace 
any engine-driven pump with signs of fuel leakage or extruding gasket 
material; and inspect to ensure that the relief valve attachment screws 
are adequately torqued and re-torque as necessary. This proposed AD is 
the result of mandatory continuing airworthiness information (MCAI) 
issued by the airworthiness authority for Switzerland. The actions 
specified by this proposed AD are intended to detect and correct gasket 
material extruding from the engine-driven pump housing and detect and 
correct relief valve attachment screws with inadequate torque. Such 
conditions could lead to fuel leakage and result in a fire in the 
engine compartment.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this proposed rule on or before November 30, 2001.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-33-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 information that applies to the proposed 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 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-33-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 of an unsafe condition that may 
exist on Pilatus Models PC-7, PC-12, and PC-12/45 airplanes. The FOCA 
reports instances of fuel leaking from the engine-driven pump on the 
referenced airplanes. The compression set of the gasket and diaphragm 
after thermal cycling could cause the gasket of the engine-driven pump 
to extrude between the relief valve housing and the engine-driven pump 
housing. This in turn relieves the torque of the relief-valve cover 
screws of the engine-driven pump, which could result in fuel leakage.
    Information on the affected pumps follows:

--The affected engine-driven pumps are Lear Romec part number RG9570R1 
(Pilatus part number 968.84.51.106) as installed on Models PC-12 and 
PC-12/45 airplanes or Lear Romec part number RG9570M1 (Pilatus part 
number 968.84.51.105) as installed on Model PC-7 airplanes;
--Pilatus installed these engine-driven pumps on manufacturer serial 
number (MSN) 101 through MSN 400 of the Models PC-12 and PC-12/45 
airplanes and MSN 101 through MSN 618 of the Model PC-7 airplanes; and
--These engine-driven pumps could be installed through field approval 
on any MSN of the Models PC-7, PC-12, and PC-12/45 airplanes.

    What are the consequences if the condition is not corrected? Gasket 
material extruding from the engine-driven pump housing and relief valve 
attachment screws with inadequate torque, if not detected and 
corrected, could lead to fuel leakage and result in a fire in the 
engine compartment.
    Is there service information that applies to this subject? Pilatus 
has issued the following:

--Service Bulletin No. 28-006, dated August 10, 2001, which applies to 
the Model PC-7 airplanes; and
--Service Bulletin No. 28-009, dated August 10, 2001, which applies to 
the Models PC-12 and PC-12/45 airplanes.


[[Page 53739]]


    What are the provisions of this service information? These service 
bulletins include procedures for:

--Inspecting the joints between the engine-driven pump housing, relief 
valve housing, and the relief-valve cover for signs of fuel leakage or 
extruding gasket material;
--Replacing any engine-driven pump with signs of fuel leakage or 
extruding gasket material; and
--Inspecting to ensure that the relief valve attachment screws are 
adequately torqued and re-torque as necessary.

    What action did the FOCA take? The FOCA classified this service 
bulletin as mandatory and issued Swiss AD HB 2001-500 (PC-12 and PC-12/
45) and Swiss AD HB-505 (PC-7), both dated August 24, 2001, in order to 
ensure the continued airworthiness of these airplanes in Switzerland.
    Was this in accordance with the bilateral airworthiness agreement? 
These airplane models are manufactured in Switzerland and are 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 Models PC-7, PC-12, and PC-12/45 airplanes of 
the same type design that are on the U.S. registry;
--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 278 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish the proposed inspections and re-torque:

----------------------------------------------------------------------------------------------------------------
                                                                                                     Total cost
                   Labor cost                                 Parts cost               Total cost      on U.S.
                                                                                      Per airplane    operators
----------------------------------------------------------------------------------------------------------------
2 workhours at $60 an hour = $120...............  Not applicable....................         $120       $33,360
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
airplanes that may need such replacement:

----------------------------------------------------------------------------------------------------------------
               Labor cost                          Parts cost                   Total cost per airplane.
----------------------------------------------------------------------------------------------------------------
1 workhour at $60 an hour = $60.........  $3,900 per new pump........  $3,960 per airplane.
----------------------------------------------------------------------------------------------------------------

Compliance Time of This Proposed AD

    What would be the compliance time of this proposed AD? The 
compliance time of the inspections that would be required by the 
proposed AD is ``within 20 hours time-in-service (TIS) after the 
effective date of this AD or within the next 30 days after the 
effective date to this AD, whichever occurs first.''
    Why is the compliance time of this proposed AD presented in both 
hours TIS and calendar time? The deterioration and potential extrusion 
of the gasket occurs over time and is not a condition of repetitive 
airplane operation. However, the relief valve attachment screws 
becoming inadequately torqued occurs as a result of airplane usage if 
the compression set of the gasket and diaphragm after thermal cycling 
causes the gasket of the engine-driven pump to extrude between the 
relief valve housing and the engine-driven pump housing.
    Therefore, to ensure that the unsafe condition defined in this 
document is detected and corrected in a timely manner, we are proposing 
the compliance in both calendar time and hours TIS.

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.

[[Page 53740]]

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-33-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

------------------------------------------------------------------------
               Model                              Serial No.
------------------------------------------------------------------------
PC-7...............................  All manufacturer serial numbers
                                      (MSN) with a Lear Romec part
                                      number RG9570M1 (Pilatus part
                                      number 968.84.51.105) engine-
                                      driven pump.
PC-12 and PC-12/45.................  All MSN with a Lear Romec part
                                      number RG9570R1 (Pilatus part
                                      number 968.84.51.106) engine-
                                      driven pump.
------------------------------------------------------------------------


    Note 1: Pilatus installed these engine-driven pumps on 
manufacturer serial number (MSN) 101 through MSN 400 of the Models 
PC-12 and PC-12/45 airplanes and MSN 101 through MSN 618 of the 
Model PC-7 airplanes. These engine-driven pumps could be installed 
through field approval on any MSN of the Models PC-7, PC-12, and PC-
12/45 airplanes;

    (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 detect and correct gasket material extruding 
from the engine-driven pump housing and detect and correct relief 
valve attachment screws with inadequate torque. Such conditions 
could lead to fuel leakage and result in a fire in the engine 
compartment.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) For all affected          Initially inspect     In accordance with
 airplanes: inspect the        within the next 20    the Accomplishment
 joints between the engine-    hours time-in-        Instructions
 driven pump housing, relief   service (TIS) after   section of either
 valve housing, and the        the effective date    Pilatus Service
 relief-valve cover for        of this AD or         Bulletin No. 28-006
 signs of fuel leakage or      within the next 30    or Pilatus Service
 extruding gasket material.    days after the        Bulletin No. 28-
                               effective date of     009, both dated
                               this AD, whichever    August 10, 2001, as
                               occurs first.         applicable.
------------------------------------------------------------------------
(2) For the Model PC-7        Replace prior to      In accordance with
 airplanes: if you find        further flight        the Accomplishment
 signs of fuel leakage or      after the             Instructions
 extruding gasket material     inspection required   section of Pilatus
 during the inspection         by paragraph (d)(1)   Service Bulletin
 required by paragraph         of this AD.           No. 28-006, dated
 (d)(1) of this AD, replace                          August 10, 2001;
 the engine-driven pump with                         and the appropriate
 a Lear Romec part number                            maintenance manual.
 RG9570M1/M engine-driven
 pump.
------------------------------------------------------------------------
(3) For the Models PC-12 and  Replace prior to      In accordance with
 PC-12/45 airplanes: if you    further flight        the Accomplishment
 find signs of fuel leakage    after the             Instructions
 or extruding gasket           inspection required   section of Pilatus
 material during the           by paragraph (d)(1)   Service Bulletin
 inspection required by        of this AD.           No. 28-009, dated
 paragraph (d)(1) of this      Accomplish the        August 10, 2001;
 AD, replace the engine-       inspection at least   and the appropriate
 driven pump with one of the   20 hours TIS after    maintenance manual.
 following and accomplish      the installation,
 any specified follow-on       but not to exceed
 action:.                      30 hours TIS after
  (i) a Lear Romec part        the installation.
 number RG95701R1/M (Pilatus
 part number 968.84.51.106/
 M) engine-driven pump; or.
  (ii) a Lear Romec part
 number RG9570R1 (Pilatus
 part number 968.84.51.106)
 engine-driven pump.
 Installation of this part
 requires you to accomplish
 the inspection specified in
 paragraph (d)(1) of this
 AD. This inspection is to
 ensure that the compression
 set of the gasket and
 diaphragm after thermal
 cycling does not cause the
 gasket of the engine-driven
 pump to extrude between the
 relief valve housing and
 the pump housing.
------------------------------------------------------------------------
(4) For all affected          Prior to further      In accordance with
 airplanes: inspect to         flight after the      the Accomplishment
 ensure that the relief        inspection required   Instructions
 valve attachment screws are   by paragraph (d)(1)   section of either
 adequately torqued and        of this AD.           Pilatus Service
 retorque as necessary.                              Bulletin No. 28-006
                                                     or Pilatus Service
                                                     Bulletin No. 28-
                                                     009, both dated
                                                     August 10, 2001, as
                                                     applicable.
------------------------------------------------------------------------
(5) Do not install, on any    As of the effective   Not Applicable.
 affected Model PC-7           date of this AD.
 airplane, a replacement
 Lear Romec part number
 RG9570M1 (Pilatus part
 number 968.84.51.105)
 engine-driven pump
------------------------------------------------------------------------

[[Page 53741]]

 
(6) If you install, on any    Accomplish the        In accordance with
 Model PC-12 or Model PC-12/   inspection at least   the Accomplishment
 45 airplane, a part number    20 hours TIS after    Instructions
 RG9570R1 (Pilatus part        the installation,     section of Pilatus
 number 968.84.51.106)         but not to exceed     Service Bulletin
 engine-driven pump, you       30 hours TIS after    No. 28-009, dated
 must accomplish the           the installation.     August 10, 2001.
 inspection specified in
 paragraph (d)(1) of this
 AD. This inspection is to
 ensure that the compression
 set of the gasket and
 diaphragm after thermal
 cycling does not cause the
 gasket of the engine-driven
 pump to extrude between the
 relief valve housing and
 the pump housing.
------------------------------------------------------------------------

    (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 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 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 obtain copies of the documents referenced in this AD from 
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; or from Pilatus Business Aircraft Ltd., Product Support 
Department, 11755 Airport Way, Broomfield, Colorado 80021. You may 
examine these documents at FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

    Note 3: The subject of this AD is addressed in Swiss AD HB 2001-
500 (PC-12 and PC-12/45) and Swiss AD HB-505 (PC-7), both dated 
August 24, 2001.


    Issued in Kansas City, Missouri, on October 16, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-26587 Filed 10-23-01; 8:45 am]
BILLING CODE 4910-13-P