Airworthiness Directives; Pilatus Aircraft Limited Model PC-6 Series Airplanes, 53920-53923 [E7-18476]
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53920
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
Model 717–200 airplanes), paragraph (j) of
AD 2006–16–15, amendment 39–14715 (for
Model MD–11 and MD–11F airplanes), or
paragraph (k) of AD 2006–16–15 (for Model
MD–10–10F and MD–10–30F airplanes),
terminates the requirements of this paragraph
for that airplane. For airplanes on which the
applicable software upgrade has been done,
the AFM revision may be removed.
‘‘Use of PROF mode for descent and/or
approach operations is prohibited unless
1. The airplane is on path and the FMA
indicates
THRUST | xxx | PROF, or
2. The indicated airspeed is below Vmax
for the airplane configuration by at least:
a. 10 knots at indicated altitudes below
10,000 feet, or
b. 15 knots at indicated altitudes of 10,000
feet or above, or
3. Basic autoflight modes (e.g., LVL CHG,
V/S, or FPA) are used to recapture the path
when the PROF mode is engaged and the
airplane is:
a. Above or below the path and the FMA
indicates PITCH | xxx | IDLE, or
b. Below the path and the FMA indicates
THRUST | xxx | V/S.’’
Note 1: When a statement identical to that
in paragraph (f) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
New Requirements of This AD
Upgrade Software—Model 717–200
Airplanes
(g) For Model 717–200 airplanes: Within
18 months after the effective date of this AD,
upgrade the versatile integrated avionics
(VIA) digital computer with new system
software (part number (P/N) PS4081970–909)
and in-service data acquisition system
(ISDAS) database (DB) software (P/N
PS4081642–909), in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 717–31–0013, dated March
25, 2005. Accomplishing this upgrade or the
installation of VIA P/N 4081570–909 or
subsequent terminates the requirements of
paragraph (f) of this AD for that airplane
only.
Note 2: Boeing Service Bulletin 717–31–
0013, dated March 25, 2005, refers to
Honeywell Alert Service Bulletin 4081570–
31–A6007, dated March 9, 2005, as an
additional source of service information for
doing the actions specified in paragraph (g)
of this AD.
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Parts Installation
(h) For Model 717–200 airplanes: As of the
effective date of this AD, no person may
install a VIA digital computer, P/N 4081570–
904, –905, –906, or –907, on any airplane,
except as required by the actions specified in
paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
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15:32 Sep 20, 2007
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(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
(j) You must use Boeing Service Bulletin
717–31–0013, dated March 25, 2005, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California
90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024), for
a copy of this service information. You may
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Renton, Washington, on
September 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–18475 Filed 9–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29178; Directorate
Identifier 2007–CE–074–AD; Amendment
39–15205; AD 2007–19–14]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above that would
supersede existing ADs. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
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This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
September 26, 2007.
On September 26, 2007, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive comments on this
AD by October 22, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
Airworthiness Directives; Pilatus
Aircraft Limited Model PC–6 Series
Airplanes
PO 00000
Findings of corrosion, wear and cracks in
the upper wing strut fittings on some PC–6
aircraft have been reported in the past.
It is possible that the spherical bearing of
the wing strut fittings installed in the
underwing can be loose in the fitting or
cannot rotate because of corrosion. In this
condition, the joint cannot function as
designed and fatigue cracks may then
develop. Undetected cracks, wear and/or
corrosion in this area could lead to failure on
the upper attachment fitting. This could
result in the failure of the wing structure
with subsequent loss of control of the
aircraft.
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You may examine the AD docket 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 AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
Discussion
On January 24, 2007, we issued AD
2007–03–08, Amendment 39–14919 (72
FR 4635; February 1, 2007), and on July
19, 2007, we issued AD 2007–15–09,
Amendment 39–15138 (72 FR 41436;
July 30, 2007). Those ADs required
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 2007–03–08 and
AD 2007–15–09, Pilatus reported that
the right hand (RH) wing strut fitting of
aircraft serial number 903 was found
with one lug shoulder completely
broken. The aircraft had accumulated
297 hours time-in-service since the RH
wing strut fitting had been replaced in
May of 2007. Based on this report, the
foreign airworthiness authority has
issued a new MCAI.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No. 2007–
0241–E, dated September 5, 2007
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Findings of corrosion, wear and cracks in
the upper wing strut fittings on some PC–6
aircraft have been reported in the past.
It is possible that the spherical bearing of
the wing strut fittings installed in the
underwing can be loose in the fitting or
cannot rotate because of corrosion. In this
condition, the joint cannot function as
designed and fatigue cracks may then
develop. Undetected cracks, wear and/or
corrosion in this area could lead to failure on
the upper attachment fitting. This could
result in the failure of the wing structure
with subsequent loss of control of the
aircraft.
To address this problem the superseded
FOCA Airworthiness Directives (AD) TM–L
Nr. 80.627–6, HB–2006–400 and EASA AD
2007–0114 were issued to mandate specific
inspections and to obtain a fleet status. Since
the issuance of AD 2007–0114, the data
reporting proved that it was necessary to
establish repetitive inspections.
Thus, in addition to an extended
applicability, the present AD mandates
repetitive inspections of the upper wing strut
fitting for cracks, wear and/or corrosion and
examination of the spherical bearing and
replacement of cracked fittings.
You may obtain further information
by examining the MCAI in the AD
docket.
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Relevant Service Information
Pilatus Aircraft Ltd. has issued
Service Bulletin No. 57–005, dated
August 30, 2007. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
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15:32 Sep 20, 2007
Jkt 211001
FAA’s Determination and Requirements
of the AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all
information provided by the State of
Design Authority and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might have also required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are described in a
separate paragraph of the AD. These
requirements take precedence over
those copied from the MCAI.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because it is possible that fatigue
cracks exist on the wing strut fittings
installed on the wing that are not
detected during the inspections
published in the aircraft maintenance
manual or required by any previous
service bulletin. Undetected cracks in
this area could lead to failure of the
fitting and consequent loss of control.
Therefore, we determined that notice
and opportunity for public comment
before issuing this AD are impracticable
and that good cause exists for making
this amendment effective in fewer than
30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
PO 00000
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53921
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2007–29178;
Directorate Identifier 2007–CE–074–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because 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
about this AD.
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 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) 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.
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53922
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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 FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14919 (72 FR
4635; February 1, 2007) and
Amendment 39–15138 (72 FR 41436;
July 30, 2007); and adding the following
new AD:
I
2007–19–14 Pilatus Aircraft Limited:
Amendment 39–15205; Docket No.
FAA–2007–29178; Directorate Identifier
2007–CE–074–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 26, 2007.
ebenthall on PROD1PC69 with RULES
Affected ADs
(b) This AD supersedes the following ADs:
(1) AD 2007–03–08; Amendment 39–
14919; and
(2) AD 2007–15–09; Amendment 39–
15138.
Applicability
(c) This AD applies to:
(1) Models PC–6, PC–6–H1, PC–6–H2, PC–
6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A,
PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/
B1–H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–
H2, and PC–6/C1–H2 airplanes (these
airplanes are also identified as Fairchild
Republic Company PC–6 airplanes, Fairchild
Industries PC–6 airplanes, Fairchild Heli
Porter PC–6 airplanes, or Fairchild-Hiller
Corporation PC–6 airplanes);
(2) Manufacturer serial numbers (MSN) 101
through 999 and MSN 2001 through 2092;
(3) Airplanes that are equipped with left
wing strut fitting part number (P/N)
6102.0041.00, P/N 111.35.06.055, P/N
111.35.06.184, or P/N 111.35.06.185; or
equipped with right wing strut fitting P/N
6102.0041.00, P/N 111.35.06.056, P/N
111.35.06.184, or P/N 111.35.06.186, or FAAapproved equivalent part numbers; and
(4) Airplanes that are certificated in any
category.
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
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15:32 Sep 20, 2007
Jkt 211001
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Findings of corrosion, wear and cracks in
the upper wing strut fittings on some PC–6
aircraft have been reported in the past.
It is possible that the spherical bearing of
the wing strut fittings installed in the
underwing can be loose in the fitting or
cannot rotate because of corrosion. In this
condition, the joint cannot function as
designed and fatigue cracks may then
develop. Undetected cracks, wear and/or
corrosion in this area could lead to failure on
the upper attachment fitting. This could
result in the failure of the wing structure
with subsequent loss of control of the
aircraft.
To address this problem the superseded
FOCA Airworthiness Directives (AD) TM–L
Nr. 80.627–6, HB–2006–400 and EASA AD
2007–0114 were issued to mandate specific
inspections and to obtain a fleet status. Since
the issuance of AD 2007–0114, the data
reporting proved that it was necessary to
establish repetitive inspections.
Thus, in addition to an extended
applicability, the present AD mandates
repetitive inspections of the upper wing strut
fitting for cracks, wear and/or corrosion and
examination of the spherical bearing and
replacement of cracked fittings.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) For airplanes that have not had both
wing strut fittings replaced within the last
100 hours time-in-service (TIS) since
September 26, 2007 (the effective date of this
AD) or inspected using an eddy current
inspection method following Pilatus Aircraft
Ltd. Service Bulletin No. 57–004, dated April
16, 2007, within the last 100 hours TIS since
September 26, 2007 (the effective date of this
AD): Before further flight after September 26,
2007 (the effective date of this AD), visually
inspect the upper wing strut fittings and
examine the spherical bearings following
Pilatus Aircraft Ltd. Service Bulletin No. 57–
005, dated August 30, 2007.
(2) For all airplanes: Within 25 hours TIS
after September 26, 2007 (the effective date
of this AD) or within 30 days after September
26, 2007 (the effective date of this AD),
whichever occurs first, visually and using
eddy current methods, inspect the upper
wing strut fittings and examine the spherical
bearings following Pilatus Aircraft Ltd.
Service Bulletin No. 57–005, dated August
30, 2007.
(3) For all airplanes: After doing the
inspection specified in paragraph (f)(2) of
this AD, repetitively at intervals not to
exceed 100 hours TIS or 3 months,
whichever occurs first, visually and using
eddy current methods, inspect the upper
wing strut fittings and examine the spherical
bearings following Pilatus Aircraft Ltd.
Service Bulletin No. 57–005, dated August
30, 2007.
(4) For all airplanes: If during any
inspection required by paragraph (f)(1), (f)(2),
or (f)(3) of this AD cracks are found in the
upper wing strut fitting, before further flight,
replace the wing strut fitting following the
PO 00000
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Fmt 4700
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Accomplishment Instructions in Pilatus
Aircraft Ltd. Service Bulletin No. 57–005,
dated August 30, 2007. Replacement of one
or both upper wing strut fitting(s) does not
terminate the repetitive inspection specified
in paragraph (f)(3) of this AD.
(5) For all airplanes: If during any
inspection required by paragraph (f)(1), (f)(2),
or (f)(3) of this AD the spherical bearing is
found not in conformity, before further flight,
replace the bearing following the
Accomplishment Instructions in Pilatus
Aircraft Ltd. Service Bulletin No. 57–005,
dated August 30, 2007.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No: 2007–0241–E,
dated September 05, 2007; Pilatus Aircraft
Ltd. Service Bulletin No. 57–005, dated
August 30, 2007; and Pilatus Aircraft Ltd.
Service Bulletin No. 57–004, dated April 16,
2007, for related information.
Material Incorporated by Reference
(i) You must use Pilatus Aircraft Ltd.
Service Bulletin No. 57–005, dated August
30, 2007, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Pilatus Aircraft Ltd.,
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Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
Customer Liaison Manager, CH 6371 STANS,
Switzerland; telephone: + 41 (0)41 619 6580;
fax: + 41 (0)41 619 6576; e-mail:
fodermatt@pilatus aircaft.com.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri on
September 13, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–18476 Filed 9–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26441; Directorate
Identifier 2006–NM–204–AD; Amendment
39–15139; AD 2007–15–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
The FAA is correcting a
typographical error in an existing
airworthiness directive (AD) that was
published in the Federal Register on
July 30, 2007 (72 FR 41438). The error
resulted in certain compliance times
being mislabeled as units of flight cycles
instead of flight hours. This AD applies
to all Boeing Model 747 airplanes. This
AD requires an inspection of the No. 2
and No. 3 windows on the left and right
sides of the airplane to determine their
part numbers, and related investigative
and corrective actions if necessary.
DATES: Effective September 21, 2007.
ADDRESSES: The AD docket contains the
proposed AD, comments, and any final
disposition. You may examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Operations office (telephone (800) 647–
5527) is located on the ground level of
the West Building at the DOT street
address stated in the ADDRESSES section.
This docket number is FAA–2006–
26441; the directorate identifier for this
docket is 2006–NM–204–AD.
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15:32 Sep 20, 2007
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Steve Fox, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6425; fax (425) 917–6590.
On July
18, 2007, the FAA issued AD 2007–15–
10, amendment 39–15139 (72 FR 41438,
July 30, 2007), for all Boeing Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes. The
AD requires an inspection of the No. 2
and No. 3 windows on the left and right
sides of the airplane to determine their
part numbers, and related investigative
and corrective actions if necessary.
As published, the compliance times
in paragraph (g) of AD 2007–15–10 were
mislabeled as units of flight cycles
instead of flight hours.
No other part of the regulatory
information has been changed;
therefore, the final rule is not
republished in the Federal Register.
The effective date of this AD remains
September 4, 2007.
SUPPLEMENTARY INFORMATION:
§ 39.13
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; correction.
AGENCY:
SUMMARY:
FOR FURTHER INFORMATION CONTACT:
[Corrected]
I In the Federal Register of July 30,
2007, on page 41441, in the 2nd
column, paragraph (g) of AD 2007–15–
10 is corrected to read as follows:
*
*
*
*
*
(g) Where Tables 1, 2, and 3 of
paragraph 1.E. of Boeing Alert Service
Bulletin 747–56A2012, dated August 24,
2006, specify counting the compliance
time from ‘‘* * * after the date on this
service bulletin,’’ this AD requires
counting the compliance time from the
effective date of this AD. After replacing
a discrepant window with a new
window, do the initial detailed
inspection of the new window at the
applicable compliance time: (1) within
5,500 flight hours after installing part
number (P/N) 65B27042–( ) or
65B27043–( ), or (2) within 22,000 flight
hours after installing P/N 65B27046–( )
or 65B27047–( ).
*
*
*
*
*
Issued in Renton, Washington, on
September 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–18472 Filed 9–20–07; 8:45 am]
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Frm 00011
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53923
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27787 Directorate
Identifier 2007–CE–032–AD; Amendment
39–15209; AD 2007–19–18]
RIN 2120–AA64
Airworthiness Directives; DG
Flugzeugbau GmbH Model DG–1000T
Gliders
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
The digital engine indicating system (DEI–
NT) and associated control unit must get
their latest software update. It has been found
out in operation, that some combinations of
system states while pressing switches can
cause electrical damages to the system. A
new software update is mandated to correct
this deficiency and to incorporate additional
safety functions to the system.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 26, 2007.
On October 26, 2007, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at Document
Management Facility, 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: Greg
Davison, Glider Program Manager, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; fax: (816)
329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
E:\FR\FM\21SER1.SGM
21SER1
]]>Agencies
[Federal Register Volume 72, Number 183 (Friday, September 21, 2007)]
[Rules and Regulations]
[Pages 53920-53923]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18476]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29178; Directorate Identifier 2007-CE-074-AD;
Amendment 39-15205; AD 2007-19-14]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Limited Model PC-6
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above that would supersede existing ADs. This AD
results from mandatory continuing airworthiness information (MCAI)
issued by the aviation authority of another country to identify and
correct an unsafe condition on an aviation product. The MCAI describes
the unsafe condition as:
Findings of corrosion, wear and cracks in the upper wing strut
fittings on some PC-6 aircraft have been reported in the past.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks, wear and/or corrosion in this area could lead to
failure on the upper attachment fitting. This could result in the
failure of the wing structure with subsequent loss of control of the
aircraft.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective September 26, 2007.
On September 26, 2007, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in this AD.
We must receive comments on this AD by October 22, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket 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 AD
docket contains this AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone (800) 647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-
4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
[[Page 53921]]
Discussion
On January 24, 2007, we issued AD 2007-03-08, Amendment 39-14919
(72 FR 4635; February 1, 2007), and on July 19, 2007, we issued AD
2007-15-09, Amendment 39-15138 (72 FR 41436; July 30, 2007). Those ADs
required actions intended to address an unsafe condition on the
products listed above.
Since we issued AD 2007-03-08 and AD 2007-15-09, Pilatus reported
that the right hand (RH) wing strut fitting of aircraft serial number
903 was found with one lug shoulder completely broken. The aircraft had
accumulated 297 hours time-in-service since the RH wing strut fitting
had been replaced in May of 2007. Based on this report, the foreign
airworthiness authority has issued a new MCAI.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2007-0241-E, dated September 5, 2007 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Findings of corrosion, wear and cracks in the upper wing strut
fittings on some PC-6 aircraft have been reported in the past.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks, wear and/or corrosion in this area could lead to
failure on the upper attachment fitting. This could result in the
failure of the wing structure with subsequent loss of control of the
aircraft.
To address this problem the superseded FOCA Airworthiness
Directives (AD) TM-L Nr. 80.627-6, HB-2006-400 and EASA AD 2007-0114
were issued to mandate specific inspections and to obtain a fleet
status. Since the issuance of AD 2007-0114, the data reporting
proved that it was necessary to establish repetitive inspections.
Thus, in addition to an extended applicability, the present AD
mandates repetitive inspections of the upper wing strut fitting for
cracks, wear and/or corrosion and examination of the spherical
bearing and replacement of cracked fittings.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Pilatus Aircraft Ltd. has issued Service Bulletin No. 57-005, dated
August 30, 2007. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are issuing this AD because we
evaluated all information provided by the State of Design Authority and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might have also required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the AD. These requirements take
precedence over those copied from the MCAI.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because it is
possible that fatigue cracks exist on the wing strut fittings installed
on the wing that are not detected during the inspections published in
the aircraft maintenance manual or required by any previous service
bulletin. Undetected cracks in this area could lead to failure of the
fitting and consequent loss of control. Therefore, we determined that
notice and opportunity for public comment before issuing this AD are
impracticable and that good cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2007-29178; Directorate
Identifier 2007-CE-074-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because 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 about this AD.
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 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) 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.
[[Page 53922]]
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 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 removing Amendment 39-14919 (72 FR
4635; February 1, 2007) and Amendment 39-15138 (72 FR 41436; July 30,
2007); and adding the following new AD:
2007-19-14 Pilatus Aircraft Limited: Amendment 39-15205; Docket No.
FAA-2007-29178; Directorate Identifier 2007-CE-074-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 26, 2007.
Affected ADs
(b) This AD supersedes the following ADs:
(1) AD 2007-03-08; Amendment 39-14919; and
(2) AD 2007-15-09; Amendment 39-15138.
Applicability
(c) This AD applies to:
(1) Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/
350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/
B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes (these
airplanes are also identified as Fairchild Republic Company PC-6
airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli
Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6
airplanes);
(2) Manufacturer serial numbers (MSN) 101 through 999 and MSN
2001 through 2092;
(3) Airplanes that are equipped with left wing strut fitting
part number (P/N) 6102.0041.00, P/N 111.35.06.055, P/N
111.35.06.184, or P/N 111.35.06.185; or equipped with right wing
strut fitting P/N 6102.0041.00, P/N 111.35.06.056, P/N
111.35.06.184, or P/N 111.35.06.186, or FAA-approved equivalent part
numbers; and
(4) Airplanes that are certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Findings of corrosion, wear and cracks in the upper wing strut
fittings on some PC-6 aircraft have been reported in the past.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks, wear and/or corrosion in this area could lead to
failure on the upper attachment fitting. This could result in the
failure of the wing structure with subsequent loss of control of the
aircraft.
To address this problem the superseded FOCA Airworthiness
Directives (AD) TM-L Nr. 80.627-6, HB-2006-400 and EASA AD 2007-0114
were issued to mandate specific inspections and to obtain a fleet
status. Since the issuance of AD 2007-0114, the data reporting
proved that it was necessary to establish repetitive inspections.
Thus, in addition to an extended applicability, the present AD
mandates repetitive inspections of the upper wing strut fitting for
cracks, wear and/or corrosion and examination of the spherical
bearing and replacement of cracked fittings.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For airplanes that have not had both wing strut fittings
replaced within the last 100 hours time-in-service (TIS) since
September 26, 2007 (the effective date of this AD) or inspected
using an eddy current inspection method following Pilatus Aircraft
Ltd. Service Bulletin No. 57-004, dated April 16, 2007, within the
last 100 hours TIS since September 26, 2007 (the effective date of
this AD): Before further flight after September 26, 2007 (the
effective date of this AD), visually inspect the upper wing strut
fittings and examine the spherical bearings following Pilatus
Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 2007.
(2) For all airplanes: Within 25 hours TIS after September 26,
2007 (the effective date of this AD) or within 30 days after
September 26, 2007 (the effective date of this AD), whichever occurs
first, visually and using eddy current methods, inspect the upper
wing strut fittings and examine the spherical bearings following
Pilatus Aircraft Ltd. Service Bulletin No. 57-005, dated August 30,
2007.
(3) For all airplanes: After doing the inspection specified in
paragraph (f)(2) of this AD, repetitively at intervals not to exceed
100 hours TIS or 3 months, whichever occurs first, visually and
using eddy current methods, inspect the upper wing strut fittings
and examine the spherical bearings following Pilatus Aircraft Ltd.
Service Bulletin No. 57-005, dated August 30, 2007.
(4) For all airplanes: If during any inspection required by
paragraph (f)(1), (f)(2), or (f)(3) of this AD cracks are found in
the upper wing strut fitting, before further flight, replace the
wing strut fitting following the Accomplishment Instructions in
Pilatus Aircraft Ltd. Service Bulletin No. 57-005, dated August 30,
2007. Replacement of one or both upper wing strut fitting(s) does
not terminate the repetitive inspection specified in paragraph
(f)(3) of this AD.
(5) For all airplanes: If during any inspection required by
paragraph (f)(1), (f)(2), or (f)(3) of this AD the spherical bearing
is found not in conformity, before further flight, replace the
bearing following the Accomplishment Instructions in Pilatus
Aircraft Ltd. Service Bulletin No. 57-005, dated August 30, 2007.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No:
2007-0241-E, dated September 05, 2007; Pilatus Aircraft Ltd. Service
Bulletin No. 57-005, dated August 30, 2007; and Pilatus Aircraft
Ltd. Service Bulletin No. 57-004, dated April 16, 2007, for related
information.
Material Incorporated by Reference
(i) You must use Pilatus Aircraft Ltd. Service Bulletin No. 57-
005, dated August 30, 2007, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Pilatus Aircraft Ltd.,
[[Page 53923]]
Customer Liaison Manager, CH 6371 STANS, Switzerland; telephone: +
41 (0)41 619 6580; fax: + 41 (0)41 619 6576; e-mail:
fodermatt@pilatusaircaft.com.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri on September 13, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-18476 Filed 9-20-07; 8:45 am]
BILLING CODE 4910-13-P
