[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]
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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.
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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:
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Total cost
Labor cost Parts cost Total cost on U.S.
Per airplane operators
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2 workhours at $60 an hour = $120............... Not applicable.................... $120 $33,360
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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.
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1 workhour at $60 an hour = $60......... $3,900 per new pump........ $3,960 per airplane.
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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:
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Actions Compliance Procedures
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(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