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

[Federal Register Volume 69, Number 32 (Wednesday, February 18, 2004)]
[Rules and Regulations]
[Pages 7560-7563]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3351]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-45-AD; Amendment 39-13481; AD 2004-04-01]
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: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) that 
supersedes 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

[[Page 7561]]

torqued and re-torque as necessary. This AD is the result of mandatory 
continuing airworthiness information (MCAI) issued by the airworthiness 
authority for Switzerland. This AD retains the actions from AD 2002-01-
09, adds certain engine-driven pumps to the applicability, and requires 
eventual replacement of the pump with an improved design pump to assure 
that the unsafe condition does not recur. We are issuing this 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: This AD becomes effective on March 29, 2004.
    On February 28, 2002 (67 FR 2323, January 17, 2002), the Director 
of the Federal Register approved the incorporation by reference of 
Pilatus PC-7 Service Bulletin No. 28-006 and Pilatus PC-12 Service 
Bulletin No. 28-009, both dated August 10, 2001.
    As of March 29, 2004, the Director of the Federal Register approved 
the incorporation by reference of the following:

    --Pilatus PC-7 Service Bulletin No. 28-007, Revision No. 1, dated 
October 1, 2002;
    --Pilatus PC-7 Service Bulletin No. 28-008, Revision 1, dated 
September 24, 2002; and
    --Pilatus PC-12 Service Bulletin No. 28-010, dated September 16, 
2002.

ADDRESSES: You may get the service information identified 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 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: --

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, 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-torqued as necessary.
    What has happened since AD 2002-01-09 to initiate this 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 FOCA 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 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 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 December 5, 2003 (68 FR 67988). The NPRM proposed 
to 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.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

    --Are consistent with 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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the 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 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 $65 per hour =      Not applicable..........            $130  $130 x 278 = $36,140.
 $130.
----------------------------------------------------------------------------------------------------------------


[[Page 7562]]

    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:

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

    What is the difference between the cost impact of this AD and the 
cost impact of AD 2002-01-09? The only difference between this 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 AD

    What is the compliance time of the inspections? The compliance time 
of the inspections that are 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 the inspections 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 you detect and correct the unsafe 
condition defined in this document is in a timely manner, we are 
stating the compliance in both calendar time and hours TIS.

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
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:

2004-04-01 Pilatus Aircraft LTD.: Amendment 39-13481; Docket No. 
2003-CE-45-AD; Supersedes AD 2002-01-09, Amendment 39-12600.

When Does This AD Become Effective?

    (a) This AD becomes effective on March 29, 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 numbers
------------------------------------------------------------------------
(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 7563]]



----------------------------------------------------------------------------------------------------------------
       Engine-driven pump P/N                      Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(i) Lear Romec P/N RG9570M1          Within the next 20 hours time-in-      Follow Pilatus PC-7 Service Bulletin
 (Pilatus P/N 968.84.51.105) or       service (TIS) after February 28,       No. 28-006 or Pilatus PC-12 Service
 Lear Romec P/N RG9570R1 (Pilatus P/  2002 (the effective date of AD 2002-   Bulletin No. 28-009, both dated
 N 968.84.51.106).                    01-09) or within the next 30 days      August 10, 2001, as applicable.
                                      after February 28, 2002 (the
                                      effective date of AD 2002-01-09),
                                      whichever occurs first, unless
                                      already done.
(ii) Lear Romec P/N RG9570M          Within the next 20 hours TIS after     Follow Pilatus PC-7 Service Bulletin
 (Pilatus P/N 968.84.51.103).         March 29, 2004 (the effective date     No. 28-008, Revision 1, dated
                                      of this AD) or within 30 days after    September 24, 2002.
                                      March 29, 2004 (the effective date
                                      of this AD), whichever occurs first,
                                      unless already done.
----------------------------------------------------------------------------------------------------------------

    (2) Replacement/Modification: Replace the engine-driven pump 
with one of the following before 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 March 29, 2004 
(the effective date of this AD) if you do not find signs of fuel 
leakage or extruding gasket material, unless already done:

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

    (3) Relief Valve Attachment Screw Torque: Before 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-
torqued 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, dated August 10, 2001.
    (4) Spares: As of March 29, 2004 (the effective date of this 
AD), install only an engine-driven pump that is a part number 
referenced in paragraphs (e)(2)(i) and (e)(2)(ii) of this AD. Before 
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 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will 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.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following 
Pilatus PC-7 Service Bulletin No. 28-006 and Pilatus PC-12 Service 
Bulletin No. 28-009, both dated August 10, 2001; Pilatus PC-7 
Service Bulletin No. 28-007, Revision No. 1, dated October 1, 2002; 
Pilatus PC-7 Service Bulletin No. 28-008, Revision 1, dated 
September 24, 2002; and Pilatus PC-12 Service Bulletin No. 28-010, 
dated September 16, 2002.
    (1) On February 28, 2002 (67 FR 2323, January 17, 2002), and in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of 
the Federal Register approved the incorporation by reference of 
Pilatus PC-7 Service Bulletin No. 28-006 and Pilatus PC-12 Service 
Bulletin No. 28-009, both dated August 10, 2001.
    (2) As of March 29, 2004, and in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51, the Director of the Federal Register approved the 
incorporation by reference of Pilatus PC-7 Service Bulletin No. 28-
007, Revision No. 1, dated October 1, 2002; Pilatus PC-7 Service 
Bulletin No. 28-008, Revision 1, dated September 24, 2002; and 
Pilatus PC-12 Service Bulletin No. 28-010, dated September 16, 2002.
    (3) You may get a copy of these documents 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 review copies at FAA, Central 
Region, Office of the Regional Counsel, 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.

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 February 10, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-3351 Filed 2-17-04; 8:45 am]
BILLING CODE 4910-13-P

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