[Federal Register Volume 87, Number 183 (Thursday, September 22, 2022)]
[Rules and Regulations]
[Pages 57809-57812]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-20517]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0153; Project Identifier MCAI-2021-01051-A;
Amendment 39-22172; AD 2022-19-03]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-26-
08, which applied to all Pilatus Aircraft Ltd. Model PC-12, PC-12/45,
PC-12/47, and PC-12/47E airplanes. AD 2016-26-08 required incorporating
revisions into the airworthiness limitations section (ALS) of the
maintenance program and inspecting the main landing gear (MLG)
attachment bolts for cracks and corrosion. Since the FAA issued AD
2016-26-08, the European Union Aviation Safety Agency (EASA) superseded
its mandatory continuing airworthiness information (MCAI) to add a new
life limit for certain MLG actuator bottom attachment bolts and then
superseded it again to add new life limits for the rudder bellcrank.
This AD requires incorporating new revisions to the ALS of the existing
airplane maintenance manual (AMM) or Instructions for Continued
Airworthiness (ICA) to establish a 5-year life limit for certain MLG
actuator bottom attachment bolts and new life limits for the rudder
bellcrank. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 27, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 27,
2022.
ADDRESSES: For service information identified in this final rule,
contact Pilatus Aircraft Ltd., CH-6371, Stans, Switzerland; phone:
+41848247365; email: aircraft.com">techsupport.ch@pilatus-aircraft.com; website:
pilatus-aircraft.com/. You may view this service information at the
FAA, Airworthiness Products Section, Operational Safety Branch, 901
Locust, Kansas City, MO 64106. For information on the availability of
this material at the FAA, call (817) 222-5110. It is also available at
regulations.gov by searching for and locating Docket No. FAA-2022-0153.
Examining the AD Docket
You may examine the AD docket at regulations.gov by searching for
and locating Docket No. FAA-2022-0153; or in person at Docket
Operations between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The AD docket contains this final rule, the MCAI, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety
Engineer, General Aviation & Rotorcraft Section, International
Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone:
(816) 329-4059; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2016-26-08, Amendment 39-18766 (82 FR 1172,
January 5, 2017; corrected February 16, 2017, 82 FR 10859) (AD 2016-26-
08). AD 2016-26-08 applied to all Pilatus Aircraft Ltd. (Pilatus) Model
PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. AD 2016-26-08
required incorporating revisions into the ALS of the existing FAA-
approved maintenance program and inspecting the MLG attachment bolts
for cracks and corrosion.
[[Page 57810]]
The NPRM published in the Federal Register on March 14, 2022 (87 FR
14187). The NPRM was prompted by reports of failure of MLG actuator
bottom attachment bolts, part number 532.10.12.218, identified with
``VLG'' on the bolt head. These parts are from a specific vendor and
are subject to hydrogen embrittlement. Accordingly, EASA, which is the
Technical Agent for the Member States of the European Union, superseded
its prior AD on this condition and issued EASA AD 2021-0005, dated
January 7, 2021, corrected January 14, 2021, to require a new 5-year
life limit for the MLG actuator bottom attachment bolt identified with
``VLG.'' Pilatus subsequently added new life limits for the rudder
bellcrank. As a result, EASA superseded its AD again and issued AD
2021-0214, dated September 17, 2021 (referred to after this as ``the
MCAI''). The MCAI states:
The airworthiness limitations and certification maintenance
instructions for Pilatus PC-12 aeroplanes, which are approved by
EASA, are currently defined and published in Pilatus PC-12 AMM
Chapter 04-00-00. These instructions have been identified as
mandatory for continued airworthiness.
Failure to accomplish these instructions could result in an
unsafe condition.
Previously, EASA issued [EASA] AD 2021-0005, requiring the
actions described in the Pilatus PC-12 AMM Chapter 04-00-00,
Document Number 02049 Issue 01 Revision 40, Document Number 02300
Issue 01 Revision 24 and Document Number 02436 Issue 01 Revision 02.
Since that [EASA] AD was issued, Pilatus published the
applicable ALS, as defined in this [EASA] AD, which contains new
and/or more restrictive tasks and limitations, as specified in the
Component Limitations section, to introduce a new life limit for the
rudder bellcrank. Due to the introduction of this life limit, the
repetitive eddy current inspections are no longer required and
deleted from the Supplemental Structural Inspection section.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2021-0005, which is superseded, and requires
accomplishment of the actions as specified in the applicable ALS.
You may examine the MCAI at regulations.gov by searching for and
locating Docket No. FAA-2022-0153.
In the NPRM, the FAA proposed to require incorporating new
revisions to the ALS of the existing AMM or ICA to establish a 5-year
life limit for certain MLG actuator bottom attachment bolts and new
life limits for the rudder bellcrank. The FAA is issuing this AD to
prevent MLG collapse during all phases of airplane operations,
including take-off and landing, and also to prevent rudder bellcrank
failure, which could lead to loss of airplane control.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from four commenters. The commenters were
the Air Line Pilots Association (ALPA), Pilatus, and two individuals.
The following presents the comments received on the NPRM and the FAA's
response to each comment.
ALPA supported the NPRM without change.
Requests Regarding the Service Information
Pilatus requested that the FAA change the proposed AD to reference
the most recent AMM revisions, which were issued December 10, 2021.
Pilatus stated that it updated the AMM, including the ALS, for
editorial changes and that requiring incorporation of the later AMM
revisions would not increase the public burden. An individual commenter
requested the FAA change the proposed AD to allow operators to comply
by incorporating later FAA-approved revisions of the ALS. The commenter
stated that not including this statement restricts operators to using
the ALS revision required by the AD, unless they obtain approval of an
alternative method of compliance (AMOC).
The FAA partially agrees. The FAA agrees to allow incorporation of
the latest revisions of the ALS, as requested by Pilatus, as an option
for compliance with paragraph (f)(1) of this AD, and has updated this
final rule accordingly. The FAA does not agree with allowing future
revisions of the ALS as an option for compliance with paragraph (f)(1)
of this AD. An AD may not refer to a document that does not exist at
the time the AD is published. The Office of the Federal Register (OFR)
regulations for approval of materials ``incorporated by reference'' in
rules require that service documents be submitted to the OFR for
approval as ``referenced material.'' An AD may reference only the
specific service document that was submitted and approved by the OFR
for incorporation by reference. The individual commenter is correct
that in order for operators to use later revisions of the referenced
document (issued after the publication of the AD), either the FAA must
revise the AD to reference the specific later revisions, or operators
must request the approval of their use as an AMOC.
Request To Increase the Average Labor Rate
An individual commenter requested the FAA adjust the average labor
rate to reflect the current economic burden. The individual stated that
the average labor rate in the NPRM is too low.
The FAA disagrees. The FAA Office of Aviation Policy and Plans
provides the labor rate of $85 per work-hour for the FAA to use when
estimating the labor costs of complying with AD requirements. The FAA
did not change this final rule based on this comment.
Additional Change Made to This Final Rule
The FAA has revised the document citations for the service
information required in this AD to adhere to OFR regulations for
materials incorporated by reference.
Conclusion
These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI referenced above. The FAA reviewed the relevant data,
considered the comments received, and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. Except for
the changes described previously, this AD is adopted as proposed in the
NPRM. None of the changes will increase the economic burden on any
operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed the following service information, which contains
the new life limit for certain MLG actuator bottom attachment bolts and
new life limits for the rudder bellcrank. These documents are distinct
because they apply to different airplane models; the different revision
levels include editorial updates.
PC-12, PC-12/45, PC-12/47 Structural, Component and
Miscellaneous Limitations--AMM Document No. 02049--Airworthiness
Limitations, Document Module Code 12-A-04-00-00-00A-000A-A, of the
Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft
Maintenance Manual Document No. 02049, Revision 41, dated July 16,
2021.
PC-12, PC-12/45, PC-12/47 Structural, Component and
Miscellaneous Limitations--AMM Document No. 02049--Airworthiness
Limitations, Document Module Code 12-A-04-00-00-00A-000A-A, of the
Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft
[[Page 57811]]
Maintenance Manual Document No. 02049, Revision 42, dated December 10,
2021.
PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 2300--Airworthiness Limitations, Document
Module Code 12-B-04-00-00-00A-000A-A, of the Pilatus Model type--PC-12/
47E MSN-545/1001-1719 and 1721-1942 Aircraft Maintenance Manual
Document No. 02300, Revision 25, dated July 16, 2021.
PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 2300--Airworthiness Limitations, Document
Module Code 12-B-04-00-00-00A-000A-A, of the Pilatus Model type--PC-12/
47E MSN-1001-1942 (except MSN 1720) Aircraft Maintenance Manual
Document No. 02300, Revision 26, dated December 10, 2021.
PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 02436--Airworthiness Limitations,
Document Module Code 12-C-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN 1720, 2001-Up Aircraft Maintenance Manual Document
No. 02436, Revision 03, dated July 16, 2021.
PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 02436--Airworthiness Limitations,
Document Module Code 12-C-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN 1720, 2001-Up Aircraft Maintenance Manual Document
No. 02436, Revision 04, dated December 10, 2021.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 1,030 airplanes of U.S.
registry. The FAA also estimates that it will take 1 work-hour per
airplane to incorporate the revised ALS into the AMM or ICA. The
average labor rate is $85 per work-hour. Based on these figures, the
FAA estimates the cost on U.S. operators to be $87,550 or $85 per
airplane.
In addition, the FAA estimates that replacing a MLG actuator bottom
attachment bolt, if necessary, will take 1 work-hour and will require
parts costing $2,140 for a cost of $2,225 per airplane.
Replacing the rudder bellcrank, if necessary, will take 3 work-
hours and will require parts costing $550 for a cost of $805 per
airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA has 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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:
0
a. Removing Airworthiness Directive 2016-26-08, Amendment 39-18766 (82
FR 1172, January 5, 2017; corrected February 16, 2017, 82 FR 10859);
and
0
b. Adding the following new airworthiness directive:
2022-19-03 Pilatus Aircraft Ltd.: Amendment 39-22172; Docket No.
FAA-2022-0153; Project Identifier MCAI-2021-01051-A.
(a) Effective Date
This airworthiness directive (AD) is effective October 27, 2022.
(b) Affected ADs
This AD replaces AD 2016-26-08, Amendment 39-18766 (82 FR 1172,
January 5, 2017; corrected February 16, 2017, 82 FR 10859).
(c) Applicability
This AD applies to Pilatus Aircraft Ltd. Model PC-12, PC-12/45,
PC-12/47, and PC-12/47E airplanes, all serial numbers, certificated
in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 2722, Rudder
Actuator; 3210, Main Landing Gear; and 3211, Main Landing Gear
Attach Section.
(e) Unsafe Condition
This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The unsafe condition in the MCAI is failure of main landing
gear (MLG) actuator bottom attachment bolts and failure to
accomplish a new life limit for the rudder bellcrank. The FAA is
issuing this AD to prevent MLG collapse during all phases of
airplane operations, including take-off and landing and also to
prevent rudder bellcrank failure, which could lead to loss of
airplane control.
(f) Actions and Compliance
(1) Before further flight, unless already done, revise the
Airworthiness Limitations section of the existing airplane
maintenance manual (AMM) or Instructions for Continued Airworthiness
for your airplane by incorporating the following documents.
(i) For Model PC-12, PC-12/45, and PC-12/47 airplanes: PC-12,
PC-12/45, PC-12/47 Structural, Component and Miscellaneous
Limitations--AMM Document No. 02049--Airworthiness Limitations,
Document Module Code 12-A-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft Maintenance
Manual Document No. 02049, Revision 41, dated July 16, 2021; or PC-
12, PC-12/45, PC-12/47 Structural, Component and Miscellaneous
Limitations--AMM Document No. 02049--Airworthiness Limitations,
Document Module Code 12-A-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft Maintenance
Manual Document No. 02049, Revision 42, dated December 10, 2021.
(ii) For Model PC-12/47E airplanes with serial numbers 545, 1001
through 1719, and 1721 through 1999: PC-12/47E Structural,
[[Page 57812]]
Component and Miscellaneous Limitations--AMM Document No. 2300--
Airworthiness Limitations, Document Module Code 12-B-04-00-00-00A-
000A-A, of the Pilatus Model type--PC-12/47E MSN-545/1001-1719 and
1721-1942 Aircraft Maintenance Manual Document No. 02300, Revision
25, dated July 16, 2021; or PC-12/47E Structural, Component and
Miscellaneous Limitations--AMM Document No. 2300--Airworthiness
Limitations, Document Module Code 12-B-04-00-00-00A-000A-A, of the
Pilatus Model type--PC-12/47E MSN-1001-1942 (except MSN 1720)
Aircraft Maintenance Manual Document No. 02300, Revision 26, dated
December 10, 2021.
(iii) For Model PC-12/47E airplanes with serial numbers 1720 and
2001 and larger: PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 02436--Airworthiness Limitations,
Document Module Code 12-C-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN 1720, 2001-Up Aircraft Maintenance Manual
Document No. 02436, Revision 03, dated July 16, 2021; or PC-12/47E
Structural, Component and Miscellaneous Limitations--AMM Document
No. 02436--Airworthiness Limitations, Document Module Code 12-C-04-
00-00-00A-000A-A, of the Pilatus Model type--PC-12/47E MSN 1720,
2001-Up Aircraft Maintenance Manual Document No. 02436, Revision 04,
dated December 10, 2021.
(2) The actions required by paragraph (f)(1) of this AD may be
performed by the owner/operator (pilot) holding at least a private
pilot certificate and must be entered into the aircraft records
showing compliance with this AD in accordance with 14 CFR 43.9(a)(1)
through (4), and 14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417, 14 CFR 121.380, or 14 CFR
135.439.
(3) After revising the airworthiness limitations required by
paragraph (f)(1) of this AD, no alternative life limits or
inspection intervals may be used unless they are approved as
provided in paragraph (g) of this AD.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the certification office, send it to the
attention of the person identified in paragraph (h)(1) of this AD
and email to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(h) Related Information
(1) For more information about this AD, contact Doug Rudolph,
Aviation Safety Engineer, General Aviation & Rotorcraft Section,
International Validation Branch, 901 Locust, Room 301, Kansas City,
MO 64106; phone: (816) 329-4059; email: [email protected].
(2) Refer to MCAI European Union Aviation Safety Agency (EASA)
AD 2021-0214, dated September 17, 2021, for more information. You
may view the EASA AD at regulations.gov in Docket No. FAA-2022-0153.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) PC-12, PC-12/45, PC-12/47 Structural, Component and
Miscellaneous Limitations--AMM Document No. 02049--Airworthiness
Limitations, Document Module Code 12-A-04-00-00-00A-000A-A, of the
Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft
Maintenance Manual Document No. 02049, Revision 41, dated July 16,
2021.
(ii) PC-12, PC-12/45, PC-12/47 Structural, Component and
Miscellaneous Limitations--AMM Document No. 02049--Airworthiness
Limitations, Document Module Code 12-A-04-00-00-00A-000A-A, of the
Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-101-888 Aircraft
Maintenance Manual Document No. 02049, Revision 42, dated December
10, 2021.
(iii) PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 2300--Airworthiness Limitations,
Document Module Code 12-B-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN-545/1001-1719 and 1721-1942 Aircraft Maintenance
Manual Document No. 02300, Revision 25, dated July 16, 2021.
(iv) PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 2300--Airworthiness Limitations,
Document Module Code 12-B-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN-1001-1942 (except MSN 1720) Aircraft Maintenance
Manual Document No. 02300, Revision 26, dated December 10, 2021.
(v) PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 02436--Airworthiness Limitations,
Document Module Code 12-C-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN 1720, 2001-Up Aircraft Maintenance Manual
Document No. 02436, Revision 03, dated July 16, 2021.
(vi) PC-12/47E Structural, Component and Miscellaneous
Limitations--AMM Document No. 02436--Airworthiness Limitations,
Document Module Code 12-C-04-00-00-00A-000A-A, of the Pilatus Model
type--PC-12/47E MSN 1720, 2001-Up Aircraft Maintenance Manual
Document No. 02436, Revision 04, dated December 10, 2021.
(3) For service information identified in this AD, contact
Pilatus Aircraft Ltd., CH-6371, Stans, Switzerland; phone:
+41848247365; email: aircraft.com">techsupport.ch@pilatus-aircraft.com; website:
pilatus-aircraft.com/.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901
Locust, Kansas City, MO 64106. For information on the availability
of this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on August 31, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-20517 Filed 9-21-22; 8:45 am]
BILLING CODE 4910-13-P