[Federal Register Volume 68, Number 234 (Friday, December 5, 2003)]
[Proposed Rules]
[Pages 67988-67991]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30256]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-45-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2002-01-09, which applies to all Pilatus Aircraft Ltd. (Pilatus) Models 
PC-7, PC-12, and PC-12/45 airplanes that incorporate a certain engine-
driven pump. AD 2002-01-09 currently requires you to inspect the joints 
between the engine-driven pump housing, the relief valve housing, and 
the relief valve cover for signs of fuel leakage and extruding gasket 
material; replace any engine-driven pump with any of the above 
problems; and 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. This proposed AD would 
retain the actions from AD 2002-01-09, would add certain engine-driven 
pumps to the applicability, and would require eventual replacement of 
the pump with an improved design pump to assure that the unsafe 
condition does not recur. We are issuing this proposed AD to detect and 
correct gasket material extruding from the engine-driven pump housing 
and detect and correct relief valve attachment screws with inadequate 
torque. These conditions could lead to fuel leakage and result in a 
fire in the engine compartment.

DATES: We must receive any comments on this proposed AD by January 6, 
2004.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
    [sbull] By mail: FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2003-CE-45-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106.
    [sbull] By fax: (816) 329-3771.
    [sbull] By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2003-CE-45-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this 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 view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-45-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

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?

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-CE-45-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it. We will date-stamp your postcard and 
mail it back to you.

Are There Any Specific Portions of This Proposed AD I Should Pay 
Attention to?

    We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. If you 
contact us through a nonwritten communication and that contact relates 
to a substantive part of this proposed AD, we will summarize the 
contact and place the summary in the docket. We will consider all 
comments received by the closing date and may amend this proposed AD in 
light of those comments and contacts.

Discussion

Has FAA Taken Any Action to This Point?

    Reports of fuel leaking from certain engine-driven pumps on Pilatus 
Models PC-7, PC-12, and PC-12/45 airplanes caused FAA to issue AD 2002-
01-09,

[[Page 67989]]

Amendment 39-12600 (67 FR 2323, January 17, 2002). AD 2002-01-09 
currently requires the following on all Pilatus Models PC-7, PC-12, and 
PC-12/45 airplanes:

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

What Has Happened Since AD 2002-01-09 To Initiate This Proposed Action?

    The Federal Office for Civil Aviation (FOCA), which is the 
airworthiness authority for Switzerland, recently notified FAA of the 
need to change AD 2002-01-09. The CAA reports that problems are 
occurring on other engine-driven pumps that could be installed on the 
affected airplanes, and that the affected airplanes should have a 
certain engine-driven pump installed to ensure this unsafe condition 
does not reoccur.

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 information:

--Pilatus PC-7 Service Bulletin No. 28-007, Revision No. 1, dated 
October 1, 2002, which includes procedures for changing the diaphragm 
and valve housing assembly of the engine-driven pump, Lear Romec part 
number (P/N) RG9570M1 (Pilatus P/N 968.84.51.105) or Lear Romec P/N 
RG9570M (Pilatus P/N 968.84.51.103). This service bulletin also 
specifies incorporating Crane Lear Romec Service Bulletin SB9570-73-002 
or Crane Lear Romec Service Bulletin RG9570-73-006;
--Pilatus PC-12 Service Bulletin No. 28-010, dated September 16, 2002, 
which includes procedures for changing the diaphragm and valve housing 
assembly of the engine-driven pump, Lear Romec P/N RG9570R1 (Pilatus P/
N 968.84.51.106). This service bulletin also specifies incorporating 
Crane Lear Romec Service Bulletin SB9570-73-002; and
--Pilatus PC-7 Service Bulletin No. 28-008, Revision 1, dated September 
24, 2002, which specifies procedures for inspecting the engine-driven 
pump, Lear Romec P/N RG9570M (Pilatus P/N 968.84.51.103) for signs of 
fuel leakage or extruding gasket material and correcting relief valve 
torque on the screws.

Does the Service Information From AD 2002-01-09 Still Apply?

    Yes. Pilatus PC-7 Service Bulletin No. 28-006 and Pilatus PC-12 
Service Bulletin No. 28-009, both dated August 10, 2001, are still 
valid and provide information on the inspection and replacement of the 
engine-driven pumps, Romec P/N RG9570M1 (Pilatus P/N 968.84.51.105) and 
Lear Romec P/N RG9570R1 (Pilatus P/N 968.84.51.106).

What Action Did the FOCA Take?

    The FOCA classified these service bulletins as mandatory and issued 
FOCA AD HB 2003-392, dated September 15, 2003; and FOCA AD HB 2003-251, 
dated June16, 2003, to ensure the continued airworthiness of these 
airplanes in Switzerland.

Did the FOCA Inform the United States Per the Bilateral Airworthiness 
Agreement?

    These Pilatus Models PC-7, PC-12, and PC-12/45 airplanes 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.
    Under this bilateral airworthiness agreement, the FOCA has kept us 
informed of the situation described above.

FAA's Determination and Requirements of This Proposed AD

What Has FAA decided?

    We have examined the FOCA's findings, reviewed all available 
information, and determined that AD action is necessary for products of 
this type design that are certificated for operation in the United 
States.
    Since the unsafe condition described previously is likely to exist 
or develop on other Pilatus Models PC-7, PC-12, and PC-12/45 airplanes 
of the same type design that are registered in the United States, we 
are proposing AD action to detect and correct gasket material extruding 
from the engine-driven pump housing and detect and correct relief valve 
attachment screws with inadequate torque. These conditions could lead 
to fuel leakage and result in a fire in the engine compartment.

What Would This Proposed AD Require?

    This proposed AD would supersede
    AD 2002-01-09 with a new AD that would:

--Retain the actions from AD 2002-01-09;
--Add certain engine-driven pumps to the applicability; and
--Require eventual replacement of the pump with an improved design pump 
to assure that the unsafe condition does not reoccur.

How Does the Revision to 14 CFR Part 39 Affect This Proposed AD?

    On July 10, 2002, we published a new version of 14 CFR part 39 (67 
FR 47997, July 22, 2002), which governs FAA's AD system. This 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

Costs of Compliance

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 per
            Labor cost                    Parts cost            airplane          Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130.  Not Applicable.......                $130  $130 x 278 = $36,140.
----------------------------------------------------------------------------------------------------------------


[[Page 67990]]

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

------------------------------------------------------------------------
                                                        Total cost per
           Labor cost                 Parts cost           airplane
------------------------------------------------------------------------
1 workhour x $65 per hour = $65.  $3,900 per new      $3,965 per
                                   pump.               airplane.
------------------------------------------------------------------------

What Is the Difference Between the Cost Impact of This Proposed AD and 
the Cost Impact of AD 2002-01-09?

    The only difference between this proposed AD and AD 2002-01-09 is 
the addition of affected engine-driven pumps. The number of airplanes 
that could have an affected pump installed and the costs associated 
with inspection and replacement are the same.

Compliance Time of This Proposed AD

What Would Be the Compliance Time of the Proposed Inspection?

    The compliance time of the inspections that would be required by 
this 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 of this AD, whichever occurs first.''
    Why Is the Compliance Time of the Proposed Inspection 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 operation 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 stating 
the compliance in both calendar time and hours TIS.

Regulatory Findings

Would This Proposed AD Impact Various Entities?

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.

Would This Proposed AD Involve a Significant Rule or Regulatory Action?

    For the reasons discussed above, I certify that this proposed AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this proposed AD 
and placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No.2003-CE-45-AD'' in your request.

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 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. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 2002-01-09, Amendment 39-12600 (67 FR 2323, January 17, 2002), and 
by adding a new AD to read as follows:

Pilatus Aircraft Ltd.: Docket No. 2003-CE-45-AD.

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by January 6, 2004.

What Other ADs Are Affected By This Action?

    (b) This AD supersedes AD 2002-01-09, Amendment 39-12600.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
               Model                             Serial Nos.
------------------------------------------------------------------------
(1) PC-7..........................  All manufacturer serial numbers
                                     (MSN) equipped with either a Lear
                                     Romec part number (P/N) RG9570M
                                     (Pilatus P/N 968.84.51.103) engine-
                                     driven pump or a Lear Romec P/N
                                     RG9570M1 (Pilatus P/N
                                     968.84.51.105) engine-driven pump.
(2) PC-12 and PC-12/45............  All MSN equipped with a Lear Romec P/
                                     N RG9570R1 (Pilatus P/N
                                     968.84.51.106) engine-driven pump.
------------------------------------------------------------------------


    Note: Pilatus installed these engine-driven pumps on MSN 101 
through MSN 406 and MSN 408 through 419 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.

What Is the Unsafe Condition Presented in This AD?

    (d) The actions specified in 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. These conditions could lead to fuel leakage and 
result in a fire in the engine compartment.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:
    (1) Inspection: Inspect the joints between the engine-driven 
pump housing, the relief valve housing, and the relief valve cover 
for signs of fuel leakage and extruding gasket material as follows:

[[Page 67991]]



------------------------------------------------------------------------
   Engine-driven pump P/N          Compliance            Procedures
------------------------------------------------------------------------
(i) Lear Romec P/N RG9570M1   Within the next 20    Follow Pilatus PC-7
 (Pilatus P/N 968.84.51.105)   hours time-in-        Service Bulletin
 or Lear Romec P/N RG9570R1    service (TIS) after   No. 28-006 or
 (Pilatus P/N 968.84.51.106).  February 28, 2002     Pilatus PC-12
                               (the effective date   Service Bulletin
                               of AD 2002-01-09)     No. 28-009, both
                               or within the next    dated August 10,
                               30 days after         2001, as
                               February 28, 2002     applicable.
                               (the effective date
                               of AD 2002-01-09),
                               whichever occurs
                               first, unless
                               already done.
(ii) Lear Romec P/N RG9570M   Within 20 hours TIS   Follow Pilatus PC-7
 (Pilatus P/N 968.84.51.103).  after the effective   Service Bulletin
                               date of this AD or    No. 28-008,
                               within 30 days        Revision 1, dated
                               after the effective   September 24, 2003.
                               date of this AD,
                               whichever occurs
                               first, unless
                               already done.
------------------------------------------------------------------------

    (2) Replacement/Modification: Replace the engine-driven pump 
with one of the following prior to further flight after the 
inspection in paragraph (e)(1) of this AD if you find signs of fuel 
leakage or extruding gasket material or within 6 months after the 
effective date of this AD if you do not find signs of fuel leakage 
or extruding gasket material, whichever occurs first, unless already 
done:

------------------------------------------------------------------------
           Models             Pump replacement P/N       Procedures
------------------------------------------------------------------------
(i) PC-7....................  Lear Romec P/N        Pilatus PC-7 Service
                               RG9570M1/M (Pilatus   Bulletin No. 28-
                               P/N 968.84.51.107).   007, Revision No.
                                                     1, dated October 1,
                                                     2002.
(ii) PC-12 and PC-12/45.....  Lear Romec P/N        Pilatus PC-12
                               RG9570R1/M (Pilatus   Service Bulletin
                               P/N 968.84.51.108).   No. 28-010, dated
                                                     September 16, 2002.
------------------------------------------------------------------------

    (3) Relief Valve Attachment Screw Torque: Prior to further 
flight after the inspection (if you find no fuel leakage or 
extruding gasket material) and replacement required by this AD, 
ensure that the relief valve attachment screws are adequately 
torqued and re-torque as necessary using the following:
    (i) For Pilatus Model PC-7 Airplanes: Pilatus PC-7 Service 
Bulletin No. 28-006, dated August 10, 2001, or Pilatus PC-7 Service 
Bulletin No. 28-008, Revision 1, dated September 24, 2002.
    (ii) For Pilatus Models PC-12 and PC-12/45 Airplanes: Pilatus 
PC-12 Service Bulletin No. 28-009, both dated August 10, 2001.
    (4) Spares: As of the effective date of this AD, only install an 
engine-driven pump that is of a part number referenced in paragraphs 
(e)(2)(i) and (e)(2)(ii) of this AD. Prior to further flight after 
installation, do the relief valve attachment screw torque check as 
required by paragraph (e)(3) of this AD.
    (5) Unless Already Done Credit: This AD retains actions from AD 
2002-01-09.
    (i) You may take inspection credit if you have one of the 
engine-driven pumps installed affected by AD 2002-01-09 and the 
specific actions are already done.
    (ii) The actions of this AD do not apply if you have one of the 
engine-driven pumps installed that is referenced in paragraphs 
(e)(2)(i) and (e)(2)(ii) of this AD.

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.13. Send your request to the Manager, Standards Office, 
Small Airplane Directorate, FAA. For information on 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.

May I Get Copies of the Documents Referenced in This AD?

    (g) 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 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 view 
these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

Is There Other Information That Relates to This Subject?

    (h) FOCA (Switzerland) AD HB 2003-392, dated September 15, 2003; 
and FOCA (Switzerland) AD HB 2003-251, dated June 16, 2003, also 
address the subject of this AD.

    Issued in Kansas City, Missouri, on November 26, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-30256 Filed 12-4-03; 8:45 am]
BILLING CODE 4910-13-P