AD 2002-01-09

[Federal Register Volume 67, Number 12 (Thursday, January 17, 2002)]
[Rules and Regulations]
[Pages 2323-2327]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-899]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-33-AD; Amendment 39-12600; AD 2002-01-09]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all Pilatus Aircraft Ltd. Models PC-7, PC-12, and PC-12/45 
airplanes that incorporate a certain engine-driven pump. This AD 
requires 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

[[Page 2324]]

torqued and re-torque as necessary. 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 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: This AD becomes effective on February 28, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
February 28, 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 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 this information at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-33-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 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 Is the Potential Impact if FAA Took No Action?

    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.

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 all 
Pilatus Aircraft Ltd. Models PC-7, PC-12, and PC-12/45 airplanes that 
incorporate a certain engine-driven pump. This proposal was published 
in the Federal Register as a notice of proposed rulemaking (NPRM) on 
October 24, 2001 (66 FR 53738). The NPRM proposed to 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.

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 278 airplanes in the U.S. 
registry.

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

    We estimate the following costs to accomplish the inspections and 
re-torque:

----------------------------------------------------------------------------------------------------------------
                                                           Total cost per
            Labor cost                  Parts cost            airplane          Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours  x  $60 per hour =     Not Applicable......               $120  $120  x  278 = $33,360.
 $120.
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    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of the 
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 X $60 per hour = $60......  $3,900 per new pump..........  $3,960 per airplane.
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[[Page 2325]]

Compliance Time of This AD

What Is the Compliance Time of This AD?

    The compliance time of the inspections that will be required by 
this 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 This 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 stating 
the compliance in both calendar time and hours TIS.

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:

2002-01-09 Pilatus Aircraft Ltd.: Amendment 39-12600; 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 numbers
------------------------------------------------------------------------
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 airplanes identified in paragraph (a) of this AD 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 airplanes: inspect    Initially inspect   In accordance with
 the joints between the engine-    within the next     the
 driven pump housing, relief       20 hours time-in-   Accomplishment
 valve housing, and the relief-    service (TIS)       Instructions
 valve cover for signs of fuel     after February      section of either
 leakage or extruding gasket       28, 2002 (the       Pilatus PC-7
 material.                         effective date      Service Bulletin
                                   the of this AD)     No. 28-006 or
                                   or within the       Pilatus PC-12
                                   next 30 days        Service Bulletin
                                   after February      No. 28-009, both
                                   28, 2002 (the       dated August 10,
                                   effective date of   2001, as
                                   this AD),           applicable.
                                   whichever occurs
                                   first.
------------------------------------------------------------------------
(2) For the Model PC-7            Replace prior to    In accordance with
 airplanes: if you find signs of   further flight      the
 fuel leakage or extruding         after the           Accomplishment
 gasket material during the        inspection          Instructions
 inspection required by            required by         section of
 paragraph (d)(1) of this AD,      paragraph (d)(1)    Pilatus PC-7
 replace the engine-driven pump    of this AD.         Service Bulletin
 with a Lear Romec part number                         No. 28-006, dated
 RG9570M1/M engine-driven pump.                        August 10, 2001;
                                                       and the
                                                       appropriate
                                                       maintenance
                                                       manual.
------------------------------------------------------------------------

[[Page 2326]]

 
(3) For the Models PC-12 and PC-  Replace prior to    In accordance with
 12/45 airplanes: if you find      further flight      the
 signs of fuel leakage or          after the           Accomplishment
 extruding gasket material         inspection          Instructions
 during the inspection required    required by         section of
 by paragraph (d)(1) of this AD,   paragraph (d)(1)    Pilatus PC-12
 replace the engine-driven pump    of this AD.         Service Bulletin
 with one of the following and     Accomplish the      No. 28-009, dated
 accomplish any specified follow-  inspection at       August 10, 2001;
 on action:.                       least 20 hours      and the
(i) a Lear Romec part number       TIS after the       appropriate
 RG95701R1/M (Pilatus part         installation, but   maintenance
 number 968.84.51.106/M) engine-   not to exceed 30    manual.
 driven pump; or.                  hours TIS after
(ii) a Lear Romec part number      the installation.
 RG9570R1 (Pilatus part number
 968.84.51.106) engine-driven
 pump. Installation of this part
 requires you to accomplish the
 inspection and replacement, if
 necessary, specified in
 paragraphs (d)(1) and (d)(3) of
 this AD, respectively. 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 airplanes:   Prior to further    In accordance with
 inspect to ensure that the        flight after the    the
 relief valve attachment screws    inspection          Accomplishment
 are adequately torqued and re-    required by         Instructions
 torque as necessary.              paragraph (d)(1)    section of either
                                   of this AD.         Pilatus PC-7
                                                       Service Bulletin
                                                       No. 28-006 or
                                                       Pilatus PC-12
                                                       Service Bulletin
                                                       No. 28-009, both
                                                       dated August 10,
                                                       2001, as
                                                       applicable.
------------------------------------------------------------------------
(5) Do not install, on any        As of February 28,  Not Applicable.
 affected Model PC-7 airplane, a   2002 (the
 replacement Lear Romec part       effective date of
 number RG9570M1 (Pilatus part     this AD).
 number 968.84.51.105) engine-
 driven pump.
------------------------------------------------------------------------
(6) If you install, on any Model  Accomplish the      In accordance with
 PC-12 or PC-12/45 airplane, a     inspection at       the
 part number RG9570R1 (Pilatus     least 20 hours      Accomplishment
 part number 968.84.51.106)        TIS after the       Instructions
 engine-driven pump, you must      installation, but   section of
 accomplish the inspection and     not to exceed 30    Pilatus PC-12
 replacement, if necessary, as     hours TIS after     Service Bulletin
 specified in paragraphs (d)(1)    the installation.   No. 28-009, dated
 and (d)(3) of this AD,                                August 10, 2001.
 respectively. 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) 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. 28-006 or Pilatus PC-12 
Service Bulletin No. 28-009, both dated August 10, 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; or from Pilatus Business Aircraft Ltd., Product 
Support Department, 11755 Airport Way, Broomfield, Colorado 80021. 
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.
    (i) When does this amendment become effective? This amendment 
becomes effective on February 28, 2002.

    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.



[[Page 2327]]


    Issued in Kansas City, Missouri, on January 8, 2002.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-899 Filed 1-16-02; 8:45 am]
BILLING CODE 4910-13-U