[Federal Register: June 6, 2003 (Volume 68, Number 109)]
[Rules and Regulations]
[Page 33840-33842]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06jn03-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-53-AD; Amendment 39-13176; AD 2003-11-17]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-
12/45 airplanes. This AD requires you to inspect the front and rear
surfaces of the pressure dome for damage and cracks, and, if necessary,
accomplish repairs. 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 damage and cracks to the pressure dome, which could
lead to rapid decompression.
DATES: This AD becomes effective on July 28, 2003.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of July
28, 2003.
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. 2002-CE-53-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 that an
unsafe condition may exist on certain Pilatus Models PC-12 and PC-12/45
airplanes. The FOCA reports that drill and/or rivet tool damage could
have occurred in areas around the edges of the rear pressure dome
during assembly of the Models PC-12 and PC-12/45 airplanes.
Pilatus has received 19 reports of damaged pressure domes. The
reported damage included nicks and scratches. This type of damage could
also occur on the forward surface of the pressure dome.
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
certain Pilatus Models PC-12 and PC-12/45 airplanes. This proposal was
published in the Federal Register as a notice of proposed rulemaking
(NPRM) on January 14, 2003 (68 FR 1802). The NPRM proposed to require
you to inspect the front and rear surfaces of the pressure dome for
damage and cracks, and, if necessary, accomplish repairs.
What Is the Potential Impact if FAA Took No Action?
The damage to the pressure dome could result in cracks in the
pressure dome and lead to rapid decompression.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. The following presents the comment received on the
proposal and FAA's response to the comment:
Comment Issue: How To Obtain a Repair Scheme Is Unclear
What Is the Commenter's Concern?
The commenter states that the current wording in the proposed AD is
incorrect and implies that the repair scheme will come from FAA.
Additionally, the commenter states that the repair scheme will come
from the manufacturer; FAA will provide approval of the repair.
What Is FAA's Response to the Concern?
We do not concur that the current wording of the proposed AD is
incorrect. Since the service information, which is referenced in the
proposed AD, does not address repairs for this type of damage, FAA has
to individually approve each repair as needed. This gives the
manufacturer the option to develop other generic repair procedures,
which were not developed at the time of the NPRM, for this type of
damage and submit them to FAA for approval. Therefore, we have not
changed the final rule AD based on this comment.
FAA's Determination
What Is FAA's Final Determination on This Issue?
We carefully reviewed all available information related to the
subject presented above and determined that air safety and the public
interest require the adoption of the rule as proposed except for the
changes discussed above and minor editorial questions. We have
determined that these changes and 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 280 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 inspection:
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Total cost
Labor cost Parts cost per Total cost on U.S. operators
airplane
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8 workhours x $60 per hour = $480. No parts required.... $480 $480 x 280 = $134,400.
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[[Page 33841]]
We estimate the following costs to accomplish any necessary repairs
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
repair:
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Total cost per
Labor cost Parts cost airplane
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16 workhours x $60 per hour = $960 No parts required... $960.
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Compliance Time of This AD
What Will Be the Compliance Time of This AD?
The compliance time of this AD is within 90 days after the
effective date of this AD, unless already accomplished.
Why Is the Compliance Time Presented in Calendar Time Instead of Hours
Time-in-Service (TIS)?
Failure of the pressure dome is only unsafe during airplane
operation. However, this unsafe condition is not a result of the number
of times the airplane is operated. The chance of this situation
occurring is the same for an airplane with 10 hours TIS as it would be
for as airplane with 500 hours TIS. For this reason, FAA has determined
that a compliance based on calendar time will be utilized in this AD in
order to assure that the unsafe condition is addressed on all airplanes
in a reasonable time period.
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
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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2003-11-17 Pilatus Aircraft Company Ltd.: Amendment 39-13176; Docket
No. 2002-CE-53-AD.
(a) What airplanes are affected by this AD? This AD affects
Models PC-12 and PC-12/45 airplanes, that are certificated in any
category, with the following serial numbers: 101 through 380, 382
through 385, 387 through 395, 398 through 406, 408, 409, 413, 415,
and 417.
(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 damage and cracks to the
pressure dome, which could lead to rapid decompression.
(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) Inspect the pressure Within the next 90 In accordance with
dome for nick/scratch days after July 28, Pilatus Aircraft
damage. 2003 (the effective Ltd. PC-12 Service
date of this AD), Bulletin No. 53-
unless already 003, Revision 1,
accomplished. dated July 26,
2002, and the
applicable
maintenance manual.
(2) If during the inspection Prior to further In accordance with
required by paragraph flight after the Pilatus Aircraft
(d)(1) of this AD, type inspection in which Ltd. PC-12 Service
``A'' or ``B'' nick/scratch the type ``A'' or Bulletin No. 53-
damage (as specified in the ``B'' nick/scratch 003, Revision 1,
service information) is damage is found. dated July 26,
found, accomplish repairs. 2002, and the
applicable
maintenance manual.
(3) If any nick or scratch Inspect for cracks In accordance with
is found that is more than prior to further Pilatus Aircraft
0.008 inches (0.2 flight and every 10 Ltd. PC-12 Service
millimeter) during the hours TIS Bulletin No. 53-
inspection required in thereafter. Obtain 003, Revision 1,
paragraph (d)(1) of this an FAA approval dated July 26,
AD, then you have type before further 2002, and the
``C'' damage and you must: flight, if cracks applicable
(i) Use a 10X magnified are found. An FAA maintenance manual.
visual inspection to approval is
inspect for cracks.. required to fly
(ii) You may fly the pressurized beyond
airplane pressurized with 90 days or 600
type ``C'' damage for 90 landings/takeoffs,
days or 600 takeoff/ whichever occurs
landings after the type first, from the
``C'' damage is found, date of the type
whichever occurs first.. ``C'' damage
(iii) After the 90 days or finding.
600 takeoff/landings
(whichever occurs first),
to fly pressurized, you
must do one of the
following:.
[[Page 33842]]
(A) Incorporate an
FAA-approved repair
scheme obtained
from the
manufacturer; or
(B) Fly the airplane
``unpressurized
only'' and continue
to inspect for
cracks every 10
hours TIS.
(iv) If any crack is
found during an
inspection required
by paragraph
(d)(3), the
airplane may not be
utilized until an
FAA-approved repair
scheme (obtained
from the
manufacturer) is
incorporated.
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Note 1: As earlier specified in this AD, flight is not permitted
if crack damage is found.
Note 2: As earlier specified in this AD, FAA approval is
required to fly pressurized beyond 90 days or 600 takeoffs/landings,
whichever occurs first, from date of repair for type ``C'' damage.
(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 Standards Office 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 Standards Office Manager.
Note 3: 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
Sec. Sec. 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 Aircraft Ltd. PC-12 Service Bulletin No. 53-003,
Revision 1, dated July 26, 2002. The Director of the Federal
Register approved this incorporation by reference under 5 U.S.C.
552(a) and 1 CFR part 51. You may get copies 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 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.
Note 4: The subject of this AD is addressed in Swiss AD Number
HB 2002-608, dated November 1, 2002.
(i) When does this amendment become effective? This amendment
becomes effective on July 28, 2003.
Issued in Kansas City, Missouri, on May 27, 2003.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-13793 Filed 6-5-03; 8:45 am]
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