AD 2001-25-10
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Pilatus Aircraft Limited | PC-12 | Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes |
| aircraft | Pilatus Aircraft Limited | PC-12/45 | Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes |
Unsafe Condition
Excessive backlash in the flap actuator internal gear system and electrical surges in the flap control system, which could lead to flap power drive-unit circuit breaker not closing during flight and current surges, potentially causing flap system failure and reduced or loss of control of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the flap actuator internal gear system for correct end-play and backlash measurements and accomplish any necessary corrective adjustments. Incorporate modifications to the flap system and install a new design FCWU with a serial number of 100,001 or higher, or FAA-approved equivalent part number. Modify the flap control wiring and install a flap power drive-unit field control panel.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 600 flight hours after the effective date of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This amendment adopts a new airworthiness directive (AD) that supersedes Airworthiness Directive (AD) 99-19-32, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-19-32 currently requires you to inspect the flap actuator internal gear system for correct end-play and backlash measurements and accomplish any corrective adjustments, as necessary. Pilatus has identified modifications for the flap system and designed and manufactured a new flap control and warning unit (FCWU) that permits the flap power drive-unit circuit breaker to close during flight. This AD requires you to modify the flap control wiring and install a flap power drive-unit field control panel. The actions specified by this AD are intended to allow the flap power drive-unit circuit breaker to close during flight and prevent current surges in the flap control system. If the pilot cannot close the circuit breaker during flight, the flight control and warning unit (FCWU) would not sense a worn actuator. Current surges in the flap control system could decrease the electrical life of the flap power drive-unit motor contactor. Both conditions have the potential for flap system failure with consequent reduced or loss of control of the airplane.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 66, Number 246 (Friday, December 21, 2001)]
[Rules and Regulations]
[Pages 65829-65832]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-31102]
[[Page 65829]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-CE-77-AD; Amendment 39-12563; AD 2001-25-10]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models 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
supersedes Airworthiness Directive (AD) 99-19-32, which applies to
certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45
airplanes. AD 99-19-32 currently requires you to inspect the flap
actuator internal gear system for correct end-play and backlash
measurements and accomplish any corrective adjustments, as necessary.
Pilatus has identified modifications for the flap system and designed
and manufactured a new flap control and warning unit (FCWU) that
permits the flap power drive-unit circuit breaker to close during
flight. This AD requires you to modify the flap control wiring and
install a flap power drive-unit field control panel. The actions
specified by this AD are intended to allow the flap power drive-unit
circuit breaker to close during flight and prevent current surges in
the flap control system. If the pilot cannot close the circuit breaker
during flight, the flight control and warning unit (FCWU) would not
sense a worn actuator. Current surges in the flap control system could
decrease the electrical life of the flap power drive-unit motor
contactor. Both conditions have the potential for flap system failure
with consequent reduced or loss of control of the airplane.
DATES: This AD becomes effective on January 25, 2002.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of
January 25, 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. 2000-CE-77-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?
Reports of excessive backlash in the flap actuators of the internal
gear system on certain Pilatus Models PC-12 and PC-12/45 airplanes
caused FAA to issue AD 99-19-32, Amendment 39-11319 (64 FR 50439,
September 17, 1999).
AD 99-19-32 currently requires you to inspect the flap actuator
internal gear system for correct end-play and backlash measurements and
accomplish any corrective adjustments, as necessary.
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, recently notified FAA of the
need to change AD 99-19-32. The FOCA reports that Pilatus has
identified modifications for the flap system and designed and
manufactured a new flap control and warning unit (FCWU) that permits
the flap power drive-unit circuit breaker to close during flight.
The previous FCWU does not allow the pilot to close the flap power
drive-unit circuit breaker during flight and the FCWU cannot sense when
a single actuator becomes worn. This could result in flap panel
distortion. The incorporation of these modifications to the flap system
and the installation of the new design FCWU, Pilatus part number FCWU
99-3, make the current end-play and backlash measurement procedures
incorrect.
Pilatus has also identified quality deficiencies with serial
numbers less than 100,001 of Pilatus part number FCWU 99-3.
In addition, the FOCA reports that electrical surges in the flap
system can decrease the electrical life of the flap power drive-unit
motor contactor. At the 40-degree flaps position, the flaps-down limit
switch (S035) operates before the flap control warning unit can stop
the extend command, which causes the flap power drive-unit's Up/Down
relay (K32) to change from the extend to the retract position. The
current in the field winding then goes in the opposite direction while
a current still flows to the motor. Electrical current to the flap
power drive-unit motor and field windings remains when the circuit
breaker (CB034) closes and the motor contactor (K31 or K670) stays
closed.
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 PC-12 and PC-12/45 airplanes. This proposal was published in
the Federal Register as a notice of proposed rulemaking (NPRM) on
September 20, 2001 (66 FR 48381). The NPRM proposed to supersede AD 99-
19-32 and proposed to require you to accomplish the following:
--Repetitively inspect the flap actuator internal gear system for
correct end-play and backlash measurements with any necessary
corrective adjustments;
--Incorporate certain modifications to the flap system and install a
new design FCWU with a serial number of 100,001 or higher, or FAA-
approved equivalent part number; and
--Modify the flap control wiring and install a flap power drive-unit
field control panel.
Accomplishment of these proposed actions as specified in the NPRM
would be required in accordance with the following:
--Pilatus PC-12 Service Bulletin No. 27-008, which incorporates the
following pages:
------------------------------------------------------------------------
Effective pages Revision level Date
------------------------------------------------------------------------
1, 2, and 11................ 2 September 13, 2000.
3 through 10 and 12 through 1 June 26, 2000
114.
------------------------------------------------------------------------
[[Page 65830]]
--Pilatus PC-12 Service Bulletin No. 27-012, dated September 13, 2000;
--Pilatus PC-12 Maintenance Manual Temporary Revision No. 27-13, dated
April 30, 2000; and
--Pilatus PC-12 Service Bulletin No. 27-011, Revision No. 1, dated
January 26, 2001.
Note: We added to the final rule Pilatus PC-12 Maintenance
Manual Temporary Revision No. 27-14 (which superseded Temporary
Revision No. 27-13), dated December 4, 2000, and Pilatus PC-12
Aircraft Maintenance Manual 27-50-03, pages 601 through 608, dated
April 30, 2000.
What Is the Potential Impact if FAA Took No Action?
These conditions, if not corrected, could cause the flap power
drive-unit circuit breaker to not close during flight and cause current
surges in the flap control system. Both conditions have the potential
for flap system failure with consequent reduced or loss of control of
the airplane.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. The following presents the comments received on the
proposal and FAA's response to each comment:
Comment Issue No. 1: The AD Is not Necessary
What is the commenter's concern? Several commenters state that the
AD is not necessary and the actions that are currently required by AD
99-19-32 are sufficient. The commenters request that FAA withdraw the
NPRM.
What is FAA's response to the concern? We do not concur that this
AD is not necessary. As previously discussed, the unsafe conditions
specified in this document, if not corrected, could cause the flap
power drive-unit circuit breaker to not close during flight and cause
current surges in the flap control system. If the pilot cannot close
the circuit breaker during flight, the flight control and warning unit
(FCWU) would not sense a worn actuator. Current surges in the flap
control system could decrease the electrical life of the flap power
drive-unit motor contactor. Both conditions have the potential for flap
system failure with consequent reduced or loss of control of the
airplane.
We are not changing the final rule as a result of these comments.
Comment Issue No. 2: Change the Compliance Time
What is the commenter's concern? One commenter suggests that FAA
change the repetitive inspection interval for the actuator backlash
from 100 hours time-in-service (TIS) to 600 hours TIS. This would
coincide with Pilatus PC-12 Service Bulletin No. 27-008 and Pilatus PC-
12 Maintenance Manual Temporary Revision No. 27-14 (which superseded
Temporary Revision No. 27-13), dated December 4, 2000, or Pilatus PC-12
Aircraft Maintenance Manual 27-50-03, pages 601 through 608, dated
April 30, 2000.
What is FAA's response to the concern? We concur with this comment.
Our intent was to make the repeat inspections at 600-hour TIS intervals
once the improved design actuators were installed.
We are changing the final rule to reflect:
--The change in repeat inspections from 100-hour TIS to 600-hour TIS
intervals; and
--Reference to Pilatus PC-12 Maintenance Manual Temporary Revision No.
27-14 (which superseded Temporary Revision No. 27-13), dated December
4, 2000, or Pilatus PC-12 Aircraft Maintenance Manual 27-50-03, pages
601 through 608, dated April 30, 2000.
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 135 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 initial
inspection of the flap actuator internal gear system for end-play and
backlash measurements. We have no way of determining the number of
corrective adjustments each owner/operator of the affected airplanes
would need to accomplish, the nature of such adjustments, or the number
of repetitive inspections each owner/operator would incur. Therefore,
the cost estimate only takes into account the cost of the proposed
initial inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
6 workhours x $60 per hour = $360.... Not Applicable....................... $360 $48,600
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to incorporate certain
modifications to the flap system and install a new design FCWU with a
serial number of 100,001 or higher:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
70 workhours x $60 per hour = $4,200.... Pilatus will provide parts at no $4,200 $567,000
cost to the owner/operator.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to modify the flap control wiring
and install a flap power drive-unit field control panel:
[[Page 65831]]
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
5 workhours x $60 per hour = $300....... Pilatus will provide parts at no $300 $40,500
cost to the owner/operator.
----------------------------------------------------------------------------------------------------------------
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 removing Airworthiness Directive (AD)
99-19-32, Amendment 39-11319 (64 FR 50439, September 17, 1999), and
adding a new AD to read as follows:
2001-25-10 Pilatus Aircraft Ltd.: Amendment 39-12563; Docket No.
2000-CE-77-AD. Supersedes AD 99-19-32, Amendment 39-11319.
(a) What airplanes are affected by this AD? This AD affects
Models PC-12 and PC-12/45 airplanes, all serial numbers, that are
certificated in any category. Carefully check paragraphs (d)(1)
through (d)(6) of this AD for the specific actions that apply to
each airplane. All airplanes will be affected by multiple actions
specified in these paragraphs.
(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
the AD are intended to allow the flap power drive-unit circuit
breaker to close during flight and prevent current surges in the
flap control system. If the pilot cannot close the circuit breaker
during flight, the flight control and warning unit (FCWU) would not
sense a worn actuator. Current surges in the flap control system
could decrease the electrical life of the flap power drive-unit
motor contactor. Both conditions have the potential for flap system
failure with consequent reduced or loss of control of the airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) For airplanes that Within the next 50 In accordance with
incorporate a manufacturer hours time-in- the Accomplishment
serial number (MSN) in the service (TIS) after Instructions
range of 101 through 320, January 25, 2002 section of Pilatus
accomplish the following:. (the effective date PC-12 Service
of this AD), unless Bulletin No. 27-
already 008, pages 1, 2,
accomplished. and 11 at the
Revision 2 level,
dated September 13,
2000; and pages 3
through 10 and 12
through 114 at the
Revision 1 level,
dated June 26,
2000. Pilatus PC-12
Service Bulletin 27-
012, dated
September 13, 2000,
also relates to
this subject.
(i) Do the modifications
and installations to
the flap system, as
specified in the
service information.
(ii) Install a new
design flap control and
warning unit (FCWU)
(Pilatus part number
FCWU 99-3) with a
serial number of
100,001 or higher, or
FAA-approved equivalent
part number.
------------------------------------------------------------------------
(2) If you accomplished the Within the next 50 In accordance with
modifications required by hours TIS after the Accomplishment
paragraph (d)(1) of this AD January 25, 2002 Instructions
in accordance with Pilatus (the effective date section of Pilatus
PC-12 Service Bulletin 27- of this AD), unless PC-12 Service
008, all pages at the already Bulletin No. 27-
Revision 1 level, dated accomplished. 008, pages 1, 2,
June 26, 2000, you only and 11 at the
have to install a new Revision 2 level,
design FCWU (Pilatus part dated September 13,
number FCWU 99-3) with a 2000; and pages 3
serial number of 100,001 or through 10 and 12
higher, or FAA-approved through 114 at the
equivalent part number.. Revision 1 level,
dated June 26,
2000. Pilatus PC-12
Service Bulletin 27-
012, dated
September 13, 2000,
also relates to
this subject.
------------------------------------------------------------------------
[[Page 65832]]
(3) For airplanes that Within the next 50 In accordance with
incorporate an MSN in the hours TIS after the Accomplishment
range of 321 through 331, January 25, 2002 Instructions
333, 335, 336, 338 through (the effective date section of Pilatus
341, 343, or 345, install a of this AD), unless PC-12 Service
new design FCWU (Pilatus already Bulletin No. 27-
part number FCWU 99-3) with accomplished. 008, pages 1, 2,
a serial number of 100,001 and 11 at the
or higher, or FAA-approved Revision 2 level,
equivalent part number.. dated September 13,
2000; and pages 3
through 10 and 12
through 114 at the
Revision 1 level,
dated June 26,
2000. Pilatus PC-12
Service Bulletin 27-
012, dated
September 13, 2000,
also relates to
this subject.
------------------------------------------------------------------------
(4) For airplanes that Within the next 50 In accordance with
incorporate an MSN in the hours TIS after the Accomplishment
range of 101 through 400, January 25, 2002 Instructions
modify the flap control (the effective date section of Pilatus
wiring and install a flap of this AD). PC-12 Service
power drive-unit field Bulletin No. 27-
control panel.. 011, Revision No.
1, dated January
26, 2001.
------------------------------------------------------------------------
(5) For all MSN airplanes, Inspect initially In accordance with
inspect the flap actuator within the next 50 the instructions in
internal gear system for hours TIS after Pilatus PC-12
correct end-play and January 25, 2002 Maintenance Manual
backlash measurements and (the effective date Temporary Revision
make any necessary of this AD) and No. 27-14 (which
corrective adjustments.. thereafter at superseded
intervals not to Temporary Revision
exceed 600 hours No. 27-13), dated
TIS. Accomplish December 4, 2000,
corrective or Pilatus PC-12
adjustments prior Aircraft
to further flight Maintenance Manual
after the 27-50-03, pages 601
inspection where through 608, dated
deficiencies are April 30, 2000, as
detected. applicable.
------------------------------------------------------------------------
(6) For all MSN airplanes, As of January 25, Not Applicable.
do not install any Pilatus 2002 (the effective
part number FCWU 99-3 that date of this AD).
has a serial number of
100,000 or less..
------------------------------------------------------------------------
Note 1: The FAA recommends that you incorporate the most up-to-
date Pilatus reports and revisions pertaining to this subject into
the Pilatus PC-12 Pilot's Operating Handbook. The most up-to-date
documents as of the issue date of this AD are Temporary Revision No.
15, Report No. 01973-001, Issued: April 3, 2000, Sections 3 and 7;
and Temporary Revision No. 32, Report No. 01973-001, Issued: January
8, 2001, Sections 2 and 3.
(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-12 Service Bulletin No. 27-008, pages 1, 2, and 11
at the Revision 2 level, dated September 13, 2000, and pages 3
through 10 and 12 through 114 at the Revision 1 level, dated June
26, 2000; Pilatus PC-12 Service Bulletin 27-012, dated September 13,
2000; Pilatus PC-12 Service Bulletin No. 27-011, Revision No. 1,
dated January 26, 2001; Pilatus PC-12 Maintenance Manual Temporary
Revision No. 27-14 (which superseded Temporary Revision No. 27-13),
dated December 4, 2000; and Pilatus PC-12 Aircraft Maintenance
Manual 27-50-03, pages 601 through 608, dated April 30, 2000. 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; 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 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 January 25, 2002.
Issued in Kansas City, Missouri, on December 11, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-31102 Filed 12-20-01; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2021-02-04
final ruleAirworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Unsafe Condition: chafing between the IFFA and the associated front inboard tension rod, which may cause corrosion of the bare rod aluminium tube and reduce aluminium thickness, leading to failure of the inboard fla...
2020-21-23
final ruleAirworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Unsafe Condition: horizontal stabilizer rear attachment bolts that had not received correct heat treatment during the manufacturing process
2020-22-05
final ruleAirworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Unsafe Condition: Seizing of a main landing gear (MLG) spring pack assembly.
2017-11-16
final ruleAirworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes
Unsafe Condition: An error within the Flight Management System (FMS) introduced into Primus APEX software Build 10 or 10.9, which could cause deviation from the correctly calculated barometric vertical navigation no...