Airworthiness Directives; Pilatus Aircraft Ltd. 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, 47716-47720 [05-16000]
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47716
Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations
section 1344 (Passenger Carrier Use),
and section 1349(b), (Adverse Personnel
Actions);
(iv) The Federal Tort Claims Act and
any other Federal tort liability statute;
(v) The Ethics in Government Act of
1978;
(vi) Internal Revenue Code of 1986,
section 1043 (Sale of Property to
Comply with Conflict-of-Interest
Requirements); and
(vii) Title 41, United States Code,
section 423 (Prohibition on Former
Official’s Acceptance of Compensation
From Contractor).
(2) Does not have any right or
expectation for Federal employment
solely on the basis of his or her detail;
(3) May not have access to any trade
secrets or to any other nonpublic
information which is of commercial
value to the private sector organization
from which he or she is detailed;
(4) Is subject to such regulations as
the President may prescribe; and
(5) Is covered by 5 U.S.C. chapter 81,
Compensation for Work Injuries, as
provided in 5 U.S.C. 3704(c).
(c) Individuals detailed under this
part may be supervised either by
Federal or private sector managers. For
example, a Federal employee on detail
to a private sector organization may be
supervised by a private sector manager.
Likewise, a private sector employee on
detail to an agency may be supervised
by a Federal manager.
(d) As provided in 5 U.S.C. 3704(d),
a private sector organization may not
charge the Federal Government, as
direct or indirect costs under a Federal
contract, for the costs of pay or benefits
paid by that private sector organization
to an employee detailed to an agency
under this part.
(e) Details may be terminated by the
agency (agency head or designee) or
private sector organization concerned
for any reason at any time.
§ 370.107 Details to small business
concerns.
(a) The head of each agency must take
such actions as may be necessary to
ensure that, of the details made to
private sector organizations in each
calendar year, at least 20 percent are to
small business concerns, in accordance
with 5 U.S.C. 3703(e)(1).
(b) Agencies must round up to the
nearest whole number when calculating
the percentage of details to small
business concerns needed to meet the
requirements of this section. For
example, if an agency detailed 11
individuals to private sector
organizations during a given year, to
meet the 20 percent requirement, that
agency must have made at least 3
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13:13 Aug 12, 2005
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(rounded up from 2.2) of these details to
small business concerns.
(c) For purposes of this section,
‘‘year’’ refers to the 12-month period
beginning on date of the enactment of
the Act, December 17, 2002, and each
succeeding 12-month period in which
any assignments are made. Assignments
‘‘made’’ in a year are those commencing
in such year, in accordance with 5
U.S.C. 3703(e)(2).
(d) Agencies that do not meet the
requirements of this section are subject
to the reporting requirements in 5 U.S.C.
3703(e)(3).
(e) An agency that makes fewer than
five details to private sector
organizations in any year is not subject
to this section.
§ 370.108
Reporting requirements.
(a) Agencies using this part must
prepare and submit to OPM semiannual
reports in accordance with 5 U.S.C.
3706 which must include:
(1) The total number of individuals
detailed to, and the total number of
individuals detailed from, the agency
during the report period;
(2) A brief description of each detail
reported under paragraph (a)(1) of this
section including:
(i) The name of the detailed
individual, and the private sector
organization and the agency (including
the specific bureau or other agency
component) to or from which such
individual was detailed;
(ii) The respective positions to and
from which the individual was detailed,
including the duties and responsibilities
and the pay grade or level associated
with each; and
(iii) The duration and objectives of the
individual’s detail; and
(3) Such other information as OPM
considers appropriate.
(b) Reports are due to OPM no later
than April 7 and October 7 of each year
for the immediately preceding 6-month
periods ending March 31 and September
30, respectively.
(c) Agencies that do not meet the
requirements of § 370.107 must prepare
and submit annual reports to Congress
in accordance with 5 U.S.C. 3703(e)(3),
as appropriate.
§ 370.109
Agency plans.
Before detailing agency employees or
receiving private sector employees
under this part, an agency must
establish an Information Technology
Exchange Program Plan. The plan must
include, but is not limited to, the
following elements:
(a) Designation of the agency officials
with authority to review and approve
details;
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(b) Estimated number of candidates
needed, both private sector and Federal
employees, to address IT workforce
needs within the agency;
(c) Criteria for the selection of agency
employees for a detail under this part.
At a minimum, each agency must:
(1) Announce the detail, including
eligibility requirements, to all eligible
employees;
(2) Provide for employee nomination
by their organization or self-nomination,
to include endorsement by their
respective supervisor;
(3) Forward nominations to
designated agency reviewing and
approving official for final selection.
(4) Consider:
(i) The extent to which the employee’s
current competencies and skills are
being utilized in the agency;
(ii) The employee’s capability to
improve, enhance, or learn skills and
acquire competencies needed in the
agency; and
(iii) The benefits to the agency which
would result from selecting the
employee for detail.
(d) Return rights and continuing
service requirements for Federal
employees returning from a detail; and
(e) Documentation and recordkeeping
requirements sufficient to allow
reconstruction of each action taken
under this part to meet agency reporting
requirements under § 370.108(a) and (b).
[FR Doc. 05–16092 Filed 8–12–05; 8:45 am]
BILLING CODE 6325–39–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20515; Directorate
Identifier 2005–CE–09–AD; Amendment 39–
14221; AD 2005–17–01]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. 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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for all
Pilatus Aircraft Ltd. (Pilatus) (also
identified as Fairchild Republic
Company and Fairchild Heli Porter)
Model PC–6 airplanes. This AD requires
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Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations
you to repetitively inspect the stabilizertrim attachment and structural
components for cracks, corrosion, and
discrepancies and replace any defective
part with a new part. This AD also
requires you to replace all Fairchild
connecting pieces, part number (P/N)
6232.0026.XX, with a Pilatus connecting
piece and requires you to replace
fittings without an index after the P/N
with an improved part. 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 defective stabilizertrim attachments and surrounding
structural components, which could
result in failure of the stabilizer-trim
attachment. This failure could lead to
loss of control of the airplane.
DATES: This AD becomes effective on
September 29, 2005.
As of September 29, 2005, the
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulation.
ADDRESSES: To get the service
information identified in this AD,
contact Pilatus Aircraft Ltd., Customer
Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619
6580; facsimile: +41 41 619 6576.
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 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2005–20515; Directorate Identifier
2005–CE–09–AD.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD?
The Federal Office for Civil Aviation
(FOCA), which is the airworthiness
authority for Switzerland, recently
notified FAA that an unsafe condition
may exist on all Pilatus Model PC–6
airplanes. The FOCA reports that the
lower attachment bracket of the
horizontal stabilizer actuator broke,
which resulted in an emergency landing
outside the airport.
The FOCA also reports two other
instances of total failure of the stabilizer
trim attachment on in-service airplanes.
What is the potential impact if FAA
took no action? If not detected and
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13:13 Aug 12, 2005
Jkt 205001
corrected, defects in the stabilizer-trim
attachment and surrounding structural
components could cause the stabilizertrim attachment to fail. This failure
could lead to loss of control of the
airplane.
Has FAA taken any action to this
point? We issued a proposal to amend
part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to all Pilatus
Model PC–6 airplanes. This proposal
was published in the Federal Register
as a notice of proposed rulemaking
(NPRM) on March 24, 2005 (70 FR
15019). The NPRM proposed to require
you to:
—Inspect the stabilizer-trim attachment
and structural components (the
fitting, the connecting piece, the
bearing fork, the bearing support
assembly, and the auxiliary frame, as
applicable) for cracks and corrosion;
—Inspect the diameters of the boltholes
on the fittings, auxiliary frame, and
connecting piece (as applicable) for
discrepancies;
—Replace any cracked, corroded, or
defective part with a new part; and
—Replace all Fairchild connecting
pieces with a Pilatus connecting
piece.
We received comments on the NPRM
requesting the following:
—Incorporate revised service to include
a procedure for replacing certain
fittings with an improved part and to
correct the allowable limits of the
actuator attachment hole diameters;
—Change the repetitive inspection
intervals; and
—Clarify the applicability of the
affected airplanes.
As a result of the above comments, we
issued a supplemental NPRM that was
published in the Federal Register on
June 14, 2005 (34401). The
Supplemental NPRM proposed to
require you to:
—Inspect the stabilizer-trim attachment
and structural components (the
fitting, the connecting piece, the
bearing fork, the bearing support
assembly, and the auxiliary frame, as
applicable) for cracks and corrosion;
—Inspect the diameters of the boltholes
on the fittings, auxiliary frame, and
connecting piece (as applicable) for
discrepancies;
—Replace any cracked part with a new
part;
—Repair or replace corroded or
defective part;
—Replace all Fairchild connecting
pieces, P/N 6232.0026.XX with a
Pilatus connecting piece. The
Fairchild part has a rivet in the
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Sfmt 4700
47717
middle that is not on the Pilatus part;
and
—Replace all fittings, P/N 116.40.06.033
without an index after the P/N with
an improved part, P/N 116.40.06.033
with an index after the P/N or P/N
116.40.06.112.
Comments
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD.
Pilatus Aircraft Ltd. submitted a
comment stating that they have no
further comments on the Supplemental
NPRM.
Comment Issue: Update Reference to
the Swiss AD
What is the commenter’s concern?
FOCA has superseded Swiss AD HB–
2005–080, effective date March 2, 2005,
with Swiss AD HB–2005–263, effective
date June 16, 2005.
The commenter requests that the
reference to the Swiss AD be changed to
incorporate the new AD number.
What is FAA’s response to the
concern? We concur with the
commenter and will change the final
rule AD action.
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
the changes discussed above and minor
editorial corrections. We have
determined that these changes and
minor corrections:
—Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
—Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Docket Information
Where can I go to view the docket
information? You may view the AD
docket that contains information
relating to this subject in person at the
DMS Docket Offices between 9 a.m. and
5 p.m. (eastern standard time), Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5227) is located on the plaza level
of the Department of Transportation
NASSIF Building at the street address
stated in ADDRESSES. You may also view
the AD docket on the Internet at
https://dms.dot.gov.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
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Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Labor cost
Parts cost
11 work hours × $65 per hour = $715 ............
Not applicable .................................................
We estimate the following costs to do
any necessary replacements that will be
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
41 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to do the inspections:
Total cost per
airplane
required based on the results of the
inspections. We have no way of
$715
Total cost per airplane to
replace all parts
Parts cost
10 work hours × $65 = $650 ............................................
$2,000 to replace all parts ...............................................
What authority does FAA have for
issuing this rulemaking action? 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 AD.
Regulatory Findings
Will this AD impact various entities?
We have 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.
Will this AD involve a significant rule
or regulatory action? 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 the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
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13:13 Aug 12, 2005
Jkt 205001
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 summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–20515;
Directorate Identifier 2005–CE–09–AD’’
in your request.
$715 × 41 = $29,315
determining the number of airplanes
that may need these replacements:
Labor cost
Authority for This Rulemaking
Total cost on U.S.
operators
$650 + $2,000 = $2,650
What Other ADs Are Affected By This
Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplanes,
all manufacturer serial numbers (MSN), that
are certificated in any category.
Note 1: These airplanes are also identified
as Fairchild Republic Company PC–6 series
airplanes and Fairchild Heli Porter PC–6
series airplanes.
Models
PART 39—AIRWORTHINESS
DIRECTIVES
(1) PC–6
(2) PC–6–H1
(3) PC–6–H2
(4) PC–6/350
(5) PC–6/350–H1
(6) PC–6/350–H2
(7) PC–6/A
(8) PC–6/A–H1
(9) PC–6/A–H2
(10) PC–6/B–H2
(11) PC–6/B1–H2
(12) PC–6/B2–H2
(13) PC–6/B2–H4
(14) PC–6/C–H2
(15) PC–6/C1–H2
1. The authority citation for part 39
continues to read as follows:
What Is the Unsafe Condition Presented in
This AD?
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. FAA amends § 39.13 by adding a
new AD to read as follows:
I
2005–17–01 Pilatus Aircraft Ltd.:
Amendment 39–14221; Docket No.
FAA–2005–20515; Directorate Identifier
2005–CE–09–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on
September 29, 2005.
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Frm 00008
Fmt 4700
Sfmt 4700
(d) This AD is the result of mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Switzerland. We are issuing this AD to detect
and correct cracks in the stabilizer-trim
attachment and surrounding structural
components, which could result in failure of
the stabilizer-trim attachment. This failure
could lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
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Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations
Actions
Compliance
(1) Inspect the following:
(i) the stabilizer-trim attachment and structural
components (fitting, connecting piece, bearing fork, bearing support assembly, and auxiliary frame, as applicable) for cracks and corrosion; and.
(ii) the diameters of the actuator attachment
bolt holes on the fittings, auxiliary frame, and
connecting piece (as applicable) for discrepancies.
(2) If cracks are found during any inspection required in paragraph (e)(1)(i) of this AD, replace the defective part with a new part.
(3) If corrosion or discrepancies are found during any inspection required in paragraphs
(e)(1)(i) and (e)(1)(ii) of this AD, do the following:
(i) replace the defective part with a new part if
the corrosion or discrepancy is beyond the
repairable limits stated in the service information; or.
(ii) repair the defective part if the corrosion or
discrepancy is within the repairable limits
stated in the service information.
(4) Replace the following:
(i) all Fairchild connecting pieces, part number
(P/N) 6232.0026.XX, with a Pilatus connecting piece, P/N 6232.0026.XX. The Fairchild part has a rivet in the middle that is not
on the Pilatus part; and.
(ii) all fittings, P/N 116.40.06.033 without an
index after the P/N, with an improved part, P/
N 116.40.06.033 with an index of ‘‘A’’ or ‘‘B’’
after the P/N or with P/N 116.40.06.112.
(5) Do not install any of the following:
(i)
Fairchild
connecting
piece,
P/N
6232.0026.XX (it has a rivet in the middle
that is not on the Pilatus part); and.
(ii) fitting, P/N 116.40.06.033, without an index
after the part number.
Procedures
Within the next 100 hours time-in-service
(TIS) after September 29, 2005 (the effective date of this AD). Repetitively inspect
thereafter at intervals not-to-exceed 3,500
hours TIS or 7 years, whichever occurs
first.
Follow Pilatus PC–6 Service Bulletin No. 53–
001, Rev. No. 1, dated June 1, 2005.
Replace the defective part before further flight
after the inspection in which cracks are
found. After each replacement, continue
with the repetitive inspection requirement in
paragraph (e)(1) of this AD.
Follow Pilatus PC–6 Service Bulletin No. 53–
001, Rev. No. 1, dated June 1, 2005.
Replace or repair the defective part before
further flight after the inspection in which
corrosion or discrepancies are found. After
each replacement or repair, continue with
the repetitive inspection requirement in
paragraph (e)(1) of this AD.
Follow Pilatus PC–6 Service Bulletin No. 53–
001, Rev. No. 1, dated June 1, 2005.
Within the next 100 hours TIS after September 29, 2005 (the effective date of this
AD). After replacement, repetitively inspect
thereafter at intervals not-to-exceed 3,500
hours TIS or 7 years, whichever occurs
first. If after the inspection required in paragraph (e)(1) of this AD, you determine that
you already have a P/N 116.40.06.033 with
an index of ‘‘A’’ or ‘‘B’’ or a P/N
116.40.06.112 installed, repetitively inspect
thereafter at intervals not-to-exceed 3,500
hours TIS or 7 years, whichever occurs first
after the part was installed.
Follow Pilatus PC–6 Service Bulletin No. 53–
001, Rev. No. 1, dated June 1, 2005.
As of September 29, 2005 (the effective date
of this AD).
Follow Pilatus PC–6 Service Bulletin No. 53–
001, Rev. No. 1, dated June 1, 2005.
Note 2: Even though not required in this
AD, the FAA recommends that you send all
defective parts to Pilatus at the address
specified in paragraph (h) of this AD. With
the part, include the aircraft serial number,
flying hours, and cycles.
Is There Other Information That Relates to
This Subject?
May I Request an Alternative Method of
Compliance?
(g) Swiss AD HB–2005–263, effective date
June 16, 2005, also addresses the subject of
this AD.
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Standards Office, Small Airplane
Directorate, FAA. For information on any
already approved alternative methods of
compliance, contact Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
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14:26 Aug 12, 2005
47719
Jkt 205001
Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
Does This AD Incorporate Any Material by
Reference?
(h) You must do the actions required by
this AD following the instructions in Pilatus
PC–6 Service Bulletin No. 53–001, Rev. No.
1, dated June 1, 2005. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
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Sfmt 4700
Customer Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 6580;
facsimile: +41 41 619 6576. To review copies
of this service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html or
call (202) 741–6030. 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 20590–001 or on the Internet
at https://dms.dot.gov. The docket number is
FAA–2005–20515; Directorate Identifier
2005–CE–09–AD.
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47720
Federal Register / Vol. 70, No. 156 / Monday, August 15, 2005 / Rules and Regulations
Issued in Kansas City, Missouri, on August
8, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–16000 Filed 8–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22073; Directorate
Identifier 2005–NM–140–AD; Amendment
39–14219; AD 2005–16–13]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace LP Model Galaxy and
Gulfstream 200 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Gulfstream Aerospace LP Model Galaxy
and Gulfstream 200 airplanes. This AD
requires a one-time general visual
inspection for any damaged wiring,
splice, connector, and pins for the fuel
standby feed pumps and replacement of
any damaged wiring, splice, connector,
or pin. This AD also requires
replacement of the power and ground
wires for the fuel standby feed pumps.
This AD results from reports of evidence
of overheating found on the feeder wires
of the left and right fuel standby feed
pumps. We are issuing this AD to detect
and correct damaged wiring for the fuel
standby feed pumps, which could result
in an ignition source in an area where
fuel vapor may be present, and a
consequent fire or explosion.
DATES: Effective Date: August 30, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 30, 2005.
We must receive comments on this
AD by October 14, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
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.
VerDate jul<14>2003
13:13 Aug 12, 2005
Jkt 205001
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• 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.
Contact Gulfstream Aerospace
Corporation, P.O. Box 2206, Mail
Station D–25, Savannah, Georgia 31402–
2206, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Administration of
Israel (CAAI), which is the
airworthiness authority for Israel,
notified us that an unsafe condition may
exist on certain Gulfstream Aerospace
LP Model Galaxy and Gulfstream 200
airplanes. The CAAI advises that, while
troubleshooting a fuel quantity
indication condition on a Model
Gulfstream 200 airplane, technicians
found evidence of overheating on the
feeder wires splice of the left fuel
standby feed pump 3Q1. Subsequent
investigation revealed a similar
condition in the wiring of the left and
right fuel standby feed pumps of four
other Model Gulfstream 200 airplanes.
This condition, if not corrected, could
result in an ignition source in an area
where fuel vapor may be present, and a
consequent fire or explosion.
The subject fuel standby feed pump
wiring on Model Galaxy airplanes is
identical to that on the affected Model
Gulfstream 200 airplanes. Therefore,
both of these models may be subject to
the same unsafe condition.
Relevant Service Information
Gulfstream Aerospace LP has issued
Alert Service Bulletin 200–28A–261,
dated June 7, 2005. The alert service
bulletin describes procedures for
performing a visual inspection of the
wiring, splice, connector, and pins for
the left (3Q1) and right (4Q1) fuel
standby feed pumps for damage, and for
replacing any damaged wiring, splice,
connector, or pin with a new wire,
splice, connector, or pin, as applicable.
Damage includes evidence of
overheating and worn or chafed
insulation. The alert service bulletin
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
also describes procedures for replacing
the power and ground wires for the fuel
standby feed pumps with 12-AmericanWire-Gauge (AWG) wires.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
The CAAI mandated the alert service
bulletin and issued Israeli airworthiness
directive 28–05–06–08, dated July 3,
2005, to ensure the continued
airworthiness of these airplanes in
Israel.
FAA’s Determination and Requirements
of This AD
These airplane models are
manufactured in Israel 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. Pursuant to this bilateral
airworthiness agreement, the CAAI has
kept the FAA informed of the situation
described above. We have examined the
CAAI’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
detect and correct any damaged wiring,
splice, connector, or pin for the fuel
standby feed pumps, which could result
in an ignition source in an area where
fuel vapor may be present, and a
consequent fire or explosion. This AD
requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the AD and Alert Service Bulletin’’.
Clarification of Inspection in the Israeli
Airworthiness Directive
The Israeli airworthiness directive
states only to ‘‘inspect’’ the wiring; it
does not define what type of inspection
should be done. We have determined
that the inspection in the Israeli
airworthiness directive should be
described as a ‘‘general visual
inspection.’’ Note 1 has been included
in this AD to define this type of
inspection.
Differences Between the AD and Alert
Service Bulletin
The Accomplishment Instructions of
Gulfstream Alert Service Bulletin 200–
28A–261, dated June 7, 2005, instruct
operators to inspect the wiring for worn
or chafed insulation; however, it gives
no repair instructions if any worn or
chafed insulation is found. This AD
requires operators to replace any wiring
E:\FR\FM\15AUR1.SGM
15AUR1
]]>Agencies
[Federal Register Volume 70, Number 156 (Monday, August 15, 2005)]
[Rules and Regulations]
[Pages 47716-47720]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16000]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD;
Amendment 39-14221; AD 2005-17-01]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. 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
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for all
Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic
Company and Fairchild Heli Porter) Model PC-6 airplanes. This AD
requires
[[Page 47717]]
you to repetitively inspect the stabilizer-trim attachment and
structural components for cracks, corrosion, and discrepancies and
replace any defective part with a new part. This AD also requires you
to replace all Fairchild connecting pieces, part number (P/N)
6232.0026.XX, with a Pilatus connecting piece and requires you to
replace fittings without an index after the P/N with an improved part.
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 defective stabilizer-trim
attachments and surrounding structural components, which could result
in failure of the stabilizer-trim attachment. This failure could lead
to loss of control of the airplane.
DATES: This AD becomes effective on September 29, 2005.
As of September 29, 2005, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576.
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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-20515; Directorate
Identifier 2005-CE-09-AD.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Federal Office for Civil
Aviation (FOCA), which is the airworthiness authority for Switzerland,
recently notified FAA that an unsafe condition may exist on all Pilatus
Model PC-6 airplanes. The FOCA reports that the lower attachment
bracket of the horizontal stabilizer actuator broke, which resulted in
an emergency landing outside the airport.
The FOCA also reports two other instances of total failure of the
stabilizer trim attachment on in-service airplanes.
What is the potential impact if FAA took no action? If not detected
and corrected, defects in the stabilizer-trim attachment and
surrounding structural components could cause the stabilizer-trim
attachment to fail. This failure could lead to loss of control of the
airplane.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all Pilatus Model PC-6 airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on March 24, 2005 (70 FR 15019). The NPRM
proposed to require you to:
--Inspect the stabilizer-trim attachment and structural components (the
fitting, the connecting piece, the bearing fork, the bearing support
assembly, and the auxiliary frame, as applicable) for cracks and
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked, corroded, or defective part with a new part; and
--Replace all Fairchild connecting pieces with a Pilatus connecting
piece.
We received comments on the NPRM requesting the following:
--Incorporate revised service to include a procedure for replacing
certain fittings with an improved part and to correct the allowable
limits of the actuator attachment hole diameters;
--Change the repetitive inspection intervals; and
--Clarify the applicability of the affected airplanes.
As a result of the above comments, we issued a supplemental NPRM
that was published in the Federal Register on June 14, 2005 (34401).
The Supplemental NPRM proposed to require you to:
--Inspect the stabilizer-trim attachment and structural components (the
fitting, the connecting piece, the bearing fork, the bearing support
assembly, and the auxiliary frame, as applicable) for cracks and
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked part with a new part;
--Repair or replace corroded or defective part;
--Replace all Fairchild connecting pieces, P/N 6232.0026.XX with a
Pilatus connecting piece. The Fairchild part has a rivet in the middle
that is not on the Pilatus part; and
--Replace all fittings, P/N 116.40.06.033 without an index after the P/
N with an improved part, P/N 116.40.06.033 with an index after the P/N
or P/N 116.40.06.112.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD.
Pilatus Aircraft Ltd. submitted a comment stating that they have no
further comments on the Supplemental NPRM.
Comment Issue: Update Reference to the Swiss AD
What is the commenter's concern? FOCA has superseded Swiss AD HB-
2005-080, effective date March 2, 2005, with Swiss AD HB-2005-263,
effective date June 16, 2005.
The commenter requests that the reference to the Swiss AD be
changed to incorporate the new AD number.
What is FAA's response to the concern? We concur with the commenter
and will change the final rule AD action.
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
determined that these changes and minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Docket Information
Where can I go to view the docket information? You may view the AD
docket that contains information relating to this subject in person at
the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard
time), Monday through Friday, except Federal holidays. The Docket
Office (telephone 1-800-647-5227) is located on the plaza level of the
Department of Transportation NASSIF Building at the street address
stated in ADDRESSES. You may also view the AD docket on the Internet at
https://dms.dot.gov.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002),
[[Page 47718]]
which governs the FAA's AD system. This regulation now includes
material that relates to altered products, special flight permits, and
alternative methods of compliance. This material previously was
included in each individual AD. Since this material is included in 14
CFR part 39, we will not include it in future AD actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 41 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the
inspections:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
11 work hours x $65 per hour = Not applicable..... $715 $715 x 41 = $29,315
$715.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspections. We have
no way of determining the number of airplanes that may need these
replacements:
----------------------------------------------------------------------------------------------------------------
Total cost per airplane to replace all
Labor cost Parts cost parts
----------------------------------------------------------------------------------------------------------------
10 work hours x $65 = $650............. $2,000 to replace all $650 + $2,000 = $2,650
parts.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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 AD.
Regulatory Findings
Will this AD impact various entities? We have 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.
Will this AD involve a significant rule or regulatory action? 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 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2005-17-01 Pilatus Aircraft Ltd.: Amendment 39-14221; Docket No.
FAA-2005-20515; Directorate Identifier 2005-CE-09-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on September 29, 2005.
What Other ADs Are Affected By This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplanes, all manufacturer
serial numbers (MSN), that are certificated in any category.
Note 1: These airplanes are also identified as Fairchild
Republic Company PC-6 series airplanes and Fairchild Heli Porter PC-
6 series airplanes.
------------------------------------------------------------------------
Models
-------------------------------------------------------------------------
(1) PC-6
(2) PC-6-H1
(3) PC-6-H2
(4) PC-6/350
(5) PC-6/350-H1
(6) PC-6/350-H2
(7) PC-6/A
(8) PC-6/A-H1
(9) PC-6/A-H2
(10) PC-6/B-H2
(11) PC-6/B1-H2
(12) PC-6/B2-H2
(13) PC-6/B2-H4
(14) PC-6/C-H2
(15) PC-6/C1-H2
------------------------------------------------------------------------
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland. We are issuing this AD to detect and correct cracks in
the stabilizer-trim attachment and surrounding structural
components, which could result in failure of the stabilizer-trim
attachment. This failure could lead to loss of control of the
airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
[[Page 47719]]
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the following:
(i) the stabilizer-trim Within the next 100 Follow Pilatus PC-6
attachment and structural hours time-in- Service Bulletin
components (fitting, service (TIS) after No. 53-001, Rev.
connecting piece, bearing September 29, 2005 No. 1, dated June
fork, bearing support (the effective date 1, 2005.
assembly, and auxiliary of this AD).
frame, as applicable) for Repetitively
cracks and corrosion; and. inspect thereafter
(ii) the diameters of the at intervals not-to-
actuator attachment bolt exceed 3,500 hours
holes on the fittings, TIS or 7 years,
auxiliary frame, and whichever occurs
connecting piece (as first.
applicable) for
discrepancies..
-----------------------------
(2) If cracks are found Replace the Follow Pilatus PC-6
during any inspection defective part Service Bulletin
required in paragraph before further No. 53-001, Rev.
(e)(1)(i) of this AD, flight after the No. 1, dated June
replace the defective part inspection in which 1, 2005.
with a new part. cracks are found.
After each
replacement,
continue with the
repetitive
inspection
requirement in
paragraph (e)(1) of
this AD.
-----------------------------
(3) If corrosion or
discrepancies are found
during any inspection
required in paragraphs
(e)(1)(i) and (e)(1)(ii) of
this AD, do the following:
(i) replace the defective Replace or repair Follow Pilatus PC-6
part with a new part if the the defective part Service Bulletin
corrosion or discrepancy is before further No. 53-001, Rev.
beyond the repairable flight after the No. 1, dated June
limits stated in the inspection in which 1, 2005.
service information; or. corrosion or
(ii) repair the defective discrepancies are
part if the corrosion or found. After each
discrepancy is within the replacement or
repairable limits stated in repair, continue
the service information.. with the repetitive
inspection
requirement in
paragraph (e)(1) of
this AD.
-----------------------------
(4) Replace the following:
(i) all Fairchild connecting Within the next 100 Follow Pilatus PC-6
pieces, part number (P/N) hours TIS after Service Bulletin
6232.0026.XX, with a September 29, 2005 No. 53-001, Rev.
Pilatus connecting piece, P/ (the effective date No. 1, dated June
N 6232.0026.XX. The of this AD). After 1, 2005.
Fairchild part has a rivet replacement,
in the middle that is not repetitively
on the Pilatus part; and. inspect thereafter
(ii) all fittings, P/N at intervals not-to-
116.40.06.033 without an exceed 3,500 hours
index after the P/N, with TIS or 7 years,
an improved part, P/N whichever occurs
116.40.06.033 with an index first. If after the
of ``A'' or ``B'' after the inspection required
P/N or with P/N in paragraph (e)(1)
116.40.06.112.. of this AD, you
determine that you
already have a P/N
116.40.06.033 with
an index of ``A''
or ``B'' or a P/N
116.40.06.112
installed,
repetitively
inspect thereafter
at intervals not-to-
exceed 3,500 hours
TIS or 7 years,
whichever occurs
first after the
part was installed.
-----------------------------
(5) Do not install any of
the following:
(i) Fairchild connecting As of September 29, Follow Pilatus PC-6
piece, P/N 6232.0026.XX (it 2005 (the effective Service Bulletin
has a rivet in the middle date of this AD). No. 53-001, Rev.
that is not on the Pilatus No. 1, dated June
part); and. 1, 2005.
(ii) fitting, P/N
116.40.06.033, without an
index after the part
number..
------------------------------------------------------------------------
Note 2: Even though not required in this AD, the FAA recommends
that you send all defective parts to Pilatus at the address
specified in paragraph (h) of this AD. With the part, include the
aircraft serial number, flying hours, and cycles.
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090.
Is There Other Information That Relates to This Subject?
(g) Swiss AD HB-2005-263, effective date June 16, 2005, also
addresses the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Pilatus PC-6 Service Bulletin No. 53-001, Rev. No.
1, dated June 1, 2005. The Director of the Federal Register approved
the incorporation by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of
this service information, contact Pilatus Aircraft Ltd., Customer
Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619
6580; facsimile: +41 41 619 6576. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. 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 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2005-20515;
Directorate Identifier 2005-CE-09-AD.
[[Page 47720]]
Issued in Kansas City, Missouri, on August 8, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-16000 Filed 8-12-05; 8:45 am]
BILLING CODE 4910-13-P
