Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7 Airplanes, 54441-54443 [E6-15342]
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Federal Register / Vol. 71, No. 179 / Friday, September 15, 2006 / Proposed Rules
54441
Actions
Compliance
Procedures
(4) You may replace the horizontal stabilizer attachment bolts and anchor nuts with the new,
modified horizontal stabilizer attachment bolts
at any time, but no later than the applicable
times specified in paragraphs (e)(2) and
(e)(3) of this AD. After installing the new,
modified horizontal stabilizer attachment
bolts, no further action is required.
As of the effective date of this AD ...................
Follow B–N Group Ltd. Modification Leaflet for
Mod NB–M–1787, Issue 1, dated August 1,
2005.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Standards Staff, FAA,
ATTN: Albert J. Mercado, Aerospace
Engineer, Small Airplane Directorate, 901
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4119; facsimile:
(816) 329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in CFR 39.19.
Related Information
(g) MCAI British AD No. G–2004–0014 R1,
Effective Date: July 29, 2005, also addresses
the subject of this AD. To get copies of the
service information referenced in this AD,
contact B–N Group Ltd., Bembridge Airport,
Isle of Wight, PO35 5PR, United Kingdom;
telephone: +44 (0) 1983 872511; fax: +44 (0)
1983 873246. To view the AD docket, go to
the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC, or on the Internet at
https://dms.dot.gov. The docket number is
Docket No. FAA–2006–25688; Directorate
Identifier 2006–CE–44–AD.
Issued in Kansas City, Missouri, on
September 11, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–7706 Filed 9–14–06; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25582; Directorate
Identifier 2006–CE–42–AD]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Model PC–7 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
ycherry on PROD1PC64 with PROPOSALS
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Model PC–
7 airplanes. This proposed AD would
require you to do repetitive eddySUMMARY:
VerDate Aug<31>2005
14:48 Sep 14, 2006
Jkt 208001
current, non-destructive inspections of
the nose skin and adjacent structure
above the left and right main landing
gear bay and repetitive visual
inspections of the forward support
structure of the floor panel for crack
damage. If you find any crack damage,
this proposed AD would require you to
contact Pilatus to obtain a repair
solution and incorporate the repair. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) issued by the airworthiness
authority for Switzerland. We are
proposing this AD to detect and correct
cracks in the nose skin and adjacent
structure above the left and right main
landing gear bay and in the forward
support structure of the floor panel.
Crack propagation in certain areas could
lead to failure of the main wing torsion
box, which could result in loss of
control.
We must receive comments on
this proposed AD by October 16, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Pilatus
Aircraft Ltd., Customer Liaison
Manager, CH–6371 Stans, Switzerland;
telephone: +41 41 619 63 19; fax: +41 41
619 6224.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
DATES:
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2006–25582; Directorate
Identifier 2006–CE–42–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
The Federal Office for Civil Aviation
(FOCA), which is the airworthiness
authority for Switzerland, notified FAA
that an unsafe condition may exist on
certain Pilatus PC–7 airplanes. The
FOCA reports crack damage in some
radii at the rear edge of the nose skin,
part number (P/N) 111.34.07.434. The
radii are adjacent to the left and right
corners at the forward edge of the floor
panel, P/N 111.34.07.530. Crack damage
can also occur in the forward support
structure of the floor panel adjacent to
the skin panel.
This condition, if not detected and
corrected, could result in crack
propagation in certain areas, which may
lead to failure of the main wing torsion
box. This failure could result in loss of
control.
Relevant Service Information
We have reviewed Pilatus PC–7
Service Bulletin No. 57–009, dated
January 29, 2004. The service
information describes procedures for
visually inspecting the forward support
E:\FR\FM\15SEP1.SGM
15SEP1
54442
Federal Register / Vol. 71, No. 179 / Friday, September 15, 2006 / Proposed Rules
structure of the floor panel and eddycurrent, non-destructive inspecting the
nose skin and adjacent structure above
the left and right main landing gear bay
for crack damage.
Foreign Airworthiness Authority
Information
The FOCA classified this service
bulletin as mandatory and issued Swiss
AD HB 2006–374, effective date August
2, 2006, to ensure the continued
airworthiness of these airplanes in
Switzerland.
These Pilatus PC–7 airplanes are
manufactured in Switzerland and are
type-certificated for operation in the
United States under the provisions of
section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement.
Under this bilateral airworthiness
agreement, the FOCA has kept us
informed of the situation described
above.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
have examined the FOCA’s findings,
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design that are certificated for
operation in the United States.
This proposed AD would require you
to do repetitive eddy-current, nondestructive inspections of the nose skin
and adjacent structure above the left and
right main landing gear bay and
repetitive visual inspections of the
forward support structure of the floor
panel for crack damage. If you find any
crack damage, this proposed AD would
require you to contact Pilatus to obtain
a repair solution and incorporate the
repair.
The applicable service bulletin specifies
repair of the nose skin only if cracks are
found exceeding limits illustrated in
Pilatus PC–7 Service Bulletin No. 57–
009, dated January 29, 2004, as does
FOCA AD HB–2006–374, effective date
August 2, 2006. This proposed AD, if
adopted, does not allow continued flight
if any crack is found. FAA policy is to
disallow airplane operation when
known cracks exist in primary structure,
unless the ability to sustain ultimate
load with these cracks is proven. The
nose skin is considered primary
structure, and the FAA has not received
any analysis to prove that ultimate load
can be sustained with cracks in this
area.
The requirements of this proposed
AD, if adopted as a final rule, would
take precedence over the provisions in
the service information.
Differences Between the FOCA AD, the
Service Information, and This Proposed
AD
FOCA AD HB–2006–374, effective
date August 2, 2006, allows continued
flight if cracks are found in the nose
skin that do not exceed certain limits.
Costs of Compliance
We estimate that this proposed AD
would affect 10 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
Total cost
per airplane
Labor cost
Parts cost
3 work-hours × $80 per hour = $240 ........................
No parts required ......................................................
Any required ‘‘upon-condition’’
repairs would vary depending upon the
damage found. Based on this, we have
no way of determining the potential
repair costs for each airplane or the
number of airplanes that would need
the repairs based on the result of the
proposed inspections.
ycherry on PROD1PC64 with PROPOSALS
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.
We are 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
VerDate Aug<31>2005
14:48 Sep 14, 2006
Jkt 208001
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Total cost
on U.S.
operators
$240
$2,400
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
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15SEP1
Federal Register / Vol. 71, No. 179 / Friday, September 15, 2006 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Pilatus Aircraft Ltd.: Docket No. FAA–2006–
25582; Directorate Identifier 2006–CE–
42–AD.
Comments Due Date
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model PC–7
airplanes, manufacturer serial numbers 101
through 618 inclusive, that are certificated in
any category.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
(a) We must receive comments on this
airworthiness directive (AD) action by
October 16, 2006.
54443
Switzerland. We are issuing this AD to detect
and correct cracks in the nose skin and
adjacent structure above the left and right
main landing gear bay and in the forward
support structure of the floor panel. Crack
propagation in certain areas could lead to
failure of the main wing torsion box. This
failure could result in loss of control.
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect:
(i) The forward area of the floor panel and
the related structure for cracks using
magnified, visual methods.
(ii) The nose skin and adjacent structure
above the left and right main landing
gear bay for cracks using eddy-current,
non-destructive methods.
(2) If crack damage is found during any inspection required by paragraph (e)(1) of this AD,
obtain an FAA-approved repair solution from
the manufacturer through the FAA at the address specified in paragraph (f) of this AD
and incorporate the repair.
Initially inspect within the next 150 hours timein-service or 6 calendar months, whichever
occurs first, after the effective date of this
AD, unless already done. Repetitively inspect thereafter at intervals specified in
paragraph 2. B. of Pilatus PC–7 Aircraft
Maintenance Manual (AMM) 05–10–00,
dated March 4, 2005.
Before further flight after any inspection in
which crack damage is found. Further flight
with crack damage is not permitted. After
incorporating the repair, repetitively inspect
as specified in paragraph (e)(1) of this AD.
Do the initial inspection following Pilatus PC–
7 Service Bulletin No. 57–009, dated January 29, 2004. Do the repetitive inspections
following the procedures in AMM 57–10–03,
dated March 4, 2005, and AMM 05–30–05,
dated February 28, 2006.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Standards Staff, FAA,
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; facsimile: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Federal Aviation Administration
Related Information
ycherry on PROD1PC64 with PROPOSALS
(g) The Federal Office for Civil Aviation
Swiss AD HB–2006–374, effective date
August 2, 2006, also addresses the subject of
this AD. To get copies of the service
information referenced in this AD, contact
Pilatus Aircraft Ltd., Customer Liaison
Manager, CH–6371 Stans, Switzerland;
telephone: +41 41 619 63 19; fax: +41 41 619
6224. To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC, or on the Internet at
https://dms.dot.gov. The docket number is
Docket No. FAA–2006–25582; Directorate
Identifier 2006–CE–42–AD.
Issued in Kansas City, Missouri, on
September 11, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–15342 Filed 9–14–06; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
14:48 Sep 14, 2006
Jkt 208001
14 CFR Part 39
[Docket No. FAA–2006–25824; Directorate
Identifier 2004–SW–23–AD]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Model S–61L, N,
R, and NM Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for the specified Sikorsky Aircraft
Corporation (Sikorsky) model
helicopters. The AD would require,
within a specified time, creating a
component history card or equivalent
record. The AD would also require
recording the hours time-in-service
(TIS) and the external lift cycles (lift
cycles) for each main gearbox input left
and right freewheel unit (IFWU)
assembly. Also, the AD would require
calculating a moving average of lift
cycles per hour TIS at specified
intervals on each IFWU assembly. The
moving average would be used to
determine if an IFWU assembly is used
in repetitive external lift (REL) or nonREL helicopter operations. If an IFWU
assembly is used in REL operations, this
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
Obtain an FAA-approved repair solution from
the manufacturer through the FAA at the
address specified in paragraph (f) of this
AD and incorporate the repair.
AD would require a repetitive
inspection, which requires a visual and
dimensional inspection of the IFWU
assembly at specified intervals. This AD
would also require recording certain
information and replacing each part that
is beyond the wear limits or that
exhibits visual surface distress with an
airworthy part. In addition, this AD
would require permanently marking the
REL IFWU camshafts and gear housings
with the letters ‘‘REL’’ on the surface of
these parts. This proposal is prompted
by an accident in which the left and
right IFWU assembly on a helicopter
slipped or disengaged resulting in both
engines overspeeding, engine
shutdowns, and loss of engine power to
the transmissions. The actions specified
by the proposed AD are intended to
prevent slipping in the IFWU assembly,
loss of engine power to the
transmissions, and subsequent loss of
control of the helicopter.
DATES: Comments must be received on
or before November 14, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
E:\FR\FM\15SEP1.SGM
15SEP1
]]>Agencies
[Federal Register Volume 71, Number 179 (Friday, September 15, 2006)]
[Proposed Rules]
[Pages 54441-54443]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-15342]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25582; Directorate Identifier 2006-CE-42-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This
proposed AD would require you to do repetitive eddy-current, non-
destructive inspections of the nose skin and adjacent structure above
the left and right main landing gear bay and repetitive visual
inspections of the forward support structure of the floor panel for
crack damage. If you find any crack damage, this proposed AD would
require you to contact Pilatus to obtain a repair solution and
incorporate the repair. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Switzerland. We are proposing this AD to detect and
correct cracks in the nose skin and adjacent structure above the left
and right main landing gear bay and in the forward support structure of
the floor panel. Crack propagation in certain areas could lead to
failure of the main wing torsion box, which could result in loss of
control.
DATES: We must receive comments on this proposed AD by October 16,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; fax: +41 41 619 6224.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-25582; Directorate Identifier 2006-CE-42-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.
Discussion
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, notified FAA that an unsafe
condition may exist on certain Pilatus PC-7 airplanes. The FOCA reports
crack damage in some radii at the rear edge of the nose skin, part
number (P/N) 111.34.07.434. The radii are adjacent to the left and
right corners at the forward edge of the floor panel, P/N
111.34.07.530. Crack damage can also occur in the forward support
structure of the floor panel adjacent to the skin panel.
This condition, if not detected and corrected, could result in
crack propagation in certain areas, which may lead to failure of the
main wing torsion box. This failure could result in loss of control.
Relevant Service Information
We have reviewed Pilatus PC-7 Service Bulletin No. 57-009, dated
January 29, 2004. The service information describes procedures for
visually inspecting the forward support
[[Page 54442]]
structure of the floor panel and eddy-current, non-destructive
inspecting the nose skin and adjacent structure above the left and
right main landing gear bay for crack damage.
Foreign Airworthiness Authority Information
The FOCA classified this service bulletin as mandatory and issued
Swiss AD HB 2006-374, effective date August 2, 2006, to ensure the
continued airworthiness of these airplanes in Switzerland.
These Pilatus PC-7 airplanes are manufactured in Switzerland and
are type-certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement.
Under this bilateral airworthiness agreement, the FOCA has kept us
informed of the situation described above.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we have examined the FOCA's
findings, evaluated all information and determined the unsafe condition
described previously is likely to exist or develop on other products of
the same type design that are certificated for operation in the United
States.
This proposed AD would require you to do repetitive eddy-current,
non-destructive inspections of the nose skin and adjacent structure
above the left and right main landing gear bay and repetitive visual
inspections of the forward support structure of the floor panel for
crack damage. If you find any crack damage, this proposed AD would
require you to contact Pilatus to obtain a repair solution and
incorporate the repair.
Differences Between the FOCA AD, the Service Information, and This
Proposed AD
FOCA AD HB-2006-374, effective date August 2, 2006, allows
continued flight if cracks are found in the nose skin that do not
exceed certain limits. The applicable service bulletin specifies repair
of the nose skin only if cracks are found exceeding limits illustrated
in Pilatus PC-7 Service Bulletin No. 57-009, dated January 29, 2004, as
does FOCA AD HB-2006-374, effective date August 2, 2006. This proposed
AD, if adopted, does not allow continued flight if any crack is found.
FAA policy is to disallow airplane operation when known cracks exist in
primary structure, unless the ability to sustain ultimate load with
these cracks is proven. The nose skin is considered primary structure,
and the FAA has not received any analysis to prove that ultimate load
can be sustained with cracks in this area.
The requirements of this proposed AD, if adopted as a final rule,
would take precedence over the provisions in the service information.
Costs of Compliance
We estimate that this proposed AD would affect 10 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost on
Labor cost Parts cost Total cost per U.S.
airplane operators
--------------------------------------------------------------------------------------------------
3 work-hours x $80 per hour = $240... No parts required....... $240 $2,400
----------------------------------------------------------------------------------------------------------------
Any required ``upon-condition'' repairs would vary depending upon
the damage found. Based on this, we have no way of determining the
potential repair costs for each airplane or the number of airplanes
that would need the repairs based on the result of the proposed
inspections.
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.
We are 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
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5227)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
[[Page 54443]]
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Pilatus Aircraft Ltd.: Docket No. FAA-2006-25582; Directorate
Identifier 2006-CE-42-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by October 16, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model PC-7 airplanes, manufacturer serial
numbers 101 through 618 inclusive, that are certificated in any
category.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland. We are issuing this AD to detect and correct cracks in
the nose skin and adjacent structure above the left and right main
landing gear bay and in the forward support structure of the floor
panel. Crack propagation in certain areas could lead to failure of
the main wing torsion box. This failure could result in loss of
control.
Compliance
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) Inspect: Initially inspect Do the initial
(i) The forward area of the within the next 150 inspection
floor panel and the related hours time-in- following Pilatus
structure for cracks using service or 6 PC-7 Service
magnified, visual methods. calendar months, Bulletin No. 57-
(ii) The nose skin and whichever occurs 009, dated January
adjacent structure above first, after the 29, 2004. Do the
the left and right main effective date of repetitive
landing gear bay for cracks this AD, unless inspections
using eddy-current, non- already done. following the
destructive methods. Repetitively procedures in AMM
inspect thereafter 57-10-03, dated
at intervals March 4, 2005, and
specified in AMM 05-30-05, dated
paragraph 2. B. of February 28, 2006.
Pilatus PC-7
Aircraft
Maintenance Manual
(AMM) 05-10-00,
dated March 4, 2005.
(2) If crack damage is found Before further Obtain an FAA-
during any inspection flight after any approved repair
required by paragraph inspection in which solution from the
(e)(1) of this AD, obtain crack damage is manufacturer
an FAA-approved repair found. Further through the FAA at
solution from the flight with crack the address
manufacturer through the damage is not specified in
FAA at the address permitted. After paragraph (f) of
specified in paragraph (f) incorporating the this AD and
of this AD and incorporate repair, incorporate the
the repair. repetitively repair.
inspect as
specified in
paragraph (e)(1) of
this AD.
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Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059;
facsimile: (816) 329-4090, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Related Information
(g) The Federal Office for Civil Aviation Swiss AD HB-2006-374,
effective date August 2, 2006, also addresses the subject of this
AD. To get copies of the service information referenced in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371
Stans, Switzerland; telephone: +41 41 619 63 19; fax: +41 41 619
6224. To view the AD docket, go to the Docket Management Facility;
U.S. Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC, or on the Internet at https://
dms.dot.gov. The docket number is Docket No. FAA-2006-25582;
Directorate Identifier 2006-CE-42-AD.
Issued in Kansas City, Missouri, on September 11, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-15342 Filed 9-14-06; 8:45 am]
BILLING CODE 4910-13-P
