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, 35778-35781 [06-5587]
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35778
Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Rules and Regulations
PART 440—WEATHERIZATION
ASSISTANCE PROGRAM FOR LOWINCOME PERSONS
1. The authority citation for part 440
continues to read as follows:
I
Authority: 42 U.S.C. 6861 et seq.; 42 U.S.C.
7101 et seq.
§ 440.1
[Amended]
2. Section 440.1 is amended by adding
the words ‘‘or to provide such persons
renewable energy systems or
technologies’’ after the words ‘‘lowincome persons,’’ where they are first
used.
I 3. Section 440.3 is amended by adding
in alphabetical order definitions of
‘‘biomass’’ and ‘‘renewable energy
system’’ to read as follows:
I
§ 440.3
Definitions.
*
*
*
*
Biomass means any organic matter
that is available on a renewable or
recurring basis, including agricultural
crops and trees, wood and wood wastes
and residues, plants (including aquatic
plants), grasses, residues, fibers, and
animal wastes, municipal wastes, and
other waste materials.
*
*
*
*
*
Renewable energy system means a
system which when installed in
connection with a dwelling—
(1) Transmits or uses solar energy,
energy derived from geothermal
deposits, energy derived from biomass
(or any other form of renewable energy
which DOE subsequently specifies
through an amendment of this part) for
the purpose of heating or cooling such
dwelling or providing hot water or
electricity for use within such dwelling;
or wind energy for nonbusiness
residential purposes; and
(2) Which meets the performance and
quality standards prescribed in § 440.21
(c) of this part.
*
*
*
*
*
I 4. Section 440.18 is amended by:
I a. Redesignating paragraphs (b)
through (e) as paragraphs (c) through (f);
I b. Adding a new paragraph (b);
I c. Amending redesignated paragraph
(c) by adding the phrase ‘‘($3,000 for
renewable energy systems)’’ after the
words ‘‘The $2,500 average’’ in the
introductory sentence.
The additions read as follows:
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*
§ 440.18
Allowable expenditures.
*
*
*
*
*
(b) The expenditure of financial
assistance provided under this part for
labor, weatherization materials, and
related matters for a renewable energy
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15:23 Jun 21, 2006
Jkt 208001
system, shall not exceed an average of
$3,000 per dwelling unit.
*
*
*
*
*
I 5. Section 440.21 is amended by:
I a. Revising paragraph (a);
I b. Redesignating paragraphs (c)
through (h) as paragraphs (d) through
(i);
I c. Adding a new paragraph (c);
I d. Amending the introductory
sentence of redesignated paragraph (e)
by removing the words ‘‘paragraph (c)’’
and adding in their place the words
‘‘paragraph (d)’’; and, in redesignated
paragraph (e)(2), by removing the words
‘‘paragraph (d)(1)’’ and adding in their
place the words ‘‘paragraph (e)(1)’’; and
I e. Amending redesignated paragraph
(g) by removing the words ‘‘paragraphs
(b) through (e)’’ and adding in their
place the words ‘‘paragraphs (b) through
(f)’’.
The revisions and additions read as
follows:
§ 440.21 Weatherization materials
standards and energy audit procedures.
(a) Paragraph (b) of this section
describes the required standards for
weatherization materials. Paragraph (c)
(1) of this section describes the
performance and quality standards for
renewable energy systems. Paragraph (c)
(2) of this section specifies the
procedures and criteria that are used for
considering a petition from a
manufacturer requesting the Secretary to
certify an item as a renewable energy
system. Paragraphs (d) and (e) of this
section describe the cost-effectiveness
tests that weatherization materials must
pass before they may be installed in an
eligible dwelling unit. Paragraph (f) of
this section lists the other energy audit
requirements that do not pertain to costeffectiveness tests of weatherization
materials. Paragraphs (g) and (h) of this
section describe the use of priority lists
and presumptively cost-effective general
heat waste reduction materials as part of
a State’s energy audit procedures.
Paragraph (i) of this section explains
that a State’s energy audit procedures
and priority lists must be re-approved
by DOE every five years.
*
*
*
*
*
(c)(1) A system or technology shall
not be considered by DOE to be a
renewable energy system under this part
unless:
(i) It will result in a reduction in oil
or natural gas consumption;
(ii) It will not result in an increased
use of any item which is known to be,
or reasonably expected to be,
environmentally hazardous or a threat
to public health or safety;
(iii) Available Federal subsidies do
not make such a specification
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unnecessary or inappropriate (in light of
the most advantageous allocation of
economic resources); and
(iv) If a combustion rated system, it
has a thermal efficiency rating of at least
75 percent; or, in the case of a solar
system, it has a thermal efficiency rating
of at least 15 percent.
(2) Any manufacturer may submit a
petition to DOE requesting the Secretary
to certify an item as a renewable energy
system.
(i) Petitions should be submitted to:
Weatherization Assistance Program,
Office of Energy Efficiency and
Renewable, Mail Stop EE–2K, 1000
Independence Avenue, SW.,
Washington, DC 20585.
(ii) A petition for certification of an
item as a renewable energy system must
be accompanied by information
demonstrating that the item meets the
criteria in paragraph (c)(1) of this
section.
(iii) DOE may publish a document in
the Federal Register that invites public
comment on a petition.
(iv) DOE shall notify the petitioner of
the Secretary’s action on the request
within one year after the filing of a
complete petition, and shall publish
notice of approvals and denials in the
Federal Register.
*
*
*
*
*
[FR Doc. E6–9858 Filed 6–21–06; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24090; Directorate
Identifier 2006–CE–16–AD; Amendment 39–
14664; AD 2006–13–11]
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), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) that
supersedes AD 2002–21–08, which
applies to certain Pilatus Aircraft Ltd
(Pilatus) Model PC–6 airplanes. AD
2002–21–08 currently requires you to
inspect the aileron assembly for correct
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22JNR1
Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Rules and Regulations
configuration and modify as necessary.
Since we issued AD 2002–21–08, the
FAA determined the action should also
apply to all the models of the PC–6
airplanes listed in the type certificate
data sheet of Type Certificate (TC) No.
7A15 that were produced in the United
States through a licensing agreement
between Pilatus and Fairchild Republic
Company (also identified as Fairchild
Industries, Fairchild Heli Porter, or
Fairchild-Hiller Corporation). In
addition, the intent of the applicability
of AD 2002–21–08 was to apply to all
the affected serial numbers of the
airplane models listed in TC No. 7A15.
This AD retains all the actions of AD
2002–21–08, adds those Fairchild
Republic Company airplanes to the
applicability of this AD, and lists the
individual specific airplane models. We
are issuing this AD to correct improper
aileron assembly configuration, which
could result in failure of the aileron
mass balance weight. Such failure could
lead to loss of control of the airplane.
This AD becomes effective on
August 7, 2006.
As of December 6, 2002 (67 FR 64520,
October 21, 2002), the Director of the
Federal Register previously approved
the incorporation by reference of Pilatus
Service Bulletin No. 62B, dated May
1967, and Pilatus Service Bulletin No.
57–001, dated December 20, 2001, in
accordance with 5 U.S.C. 552(a) and 1
CFR part 51.
DATES:
For service information
identified in this AD, contact Pilatus
Aircraft Ltd., Customer Liaison
Manager, CH–6371 Stans, Switzerland;
telephone: +41 41 619 63 19; facsimile:
+41 41 619 6224.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–24090; Directorate Identifier
2006–CE–16–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:
ADDRESSES:
Discussion
On April 17, 2006, 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
the models of the PC–6 airplanes listed
in the type certificate data sheet of TC
No. 7A15 that are produced in the
United States through a licensing
agreement between Pilatus and
Fairchild Republic Company (also
identified as Fairchild Industries,
Fairchild Heli Porter, or Fairchild-Hiller
Corporation) airplanes. This proposal
was published in the Federal Register
as a notice of proposed rulemaking
35779
(NPRM) on April 21, 2006 (71 FR
20597). The NPRM proposed to
supersede AD 2002–21–08, Amendment
39–12914 (67 FR 64520, October 21,
2002), add those Fairchild Republic
Company airplanes to the applicability
of this proposed AD, and list the
individual specific airplane models. The
NPRM proposed to retain all the actions
of AD 2002–21–08 for inspecting and
modifying the aileron assembly.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received one comment in
favor of the proposed AD.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these 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.
Costs of Compliance
We estimate that this AD affects 49
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Labor cost
Parts cost
Total cost per
airplane
Total cost on U.S.
operators
1 work-hour × $80 per hour = $80 ...........................................................................
Not Applicable ...........
$80
49 × $80 = $3,920.
We estimate the following costs to do
any necessary modifications that would
be required based on the results of the
inspection. We have no way of
determining the number of airplanes
that may need such modification:
Labor cost
Parts cost
16 work-hours × $80 per hour = $1,280 ............................................................................................
$419
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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
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15:23 Jun 21, 2006
Jkt 208001
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
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
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Fmt 4700
Sfmt 4700
Total cost per airplane
$1,280 + $419 = $1,699.
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 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
E:\FR\FM\22JNR1.SGM
22JNR1
35780
Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Rules and Regulations
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–2006–24090;
Directorate Identifier 2006–CE–16–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
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
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. FAA amends § 39.13 by removing
Airworthiness Directive (AD) 2002–21–
08, Amendment 39–12914 (67 FR
64520, October 21, 2002), and by adding
the following new AD:
I
2006–13–11 Pilatus Aircraft Ltd.:
Amendment 39–14664; Docket No.
FAA–2006–24090; Directorate Identifier
2006–CE–16–AD.
Effective Date
(a) This AD becomes effective on August 7,
2006.
Affected ADs
(b) This AD supersedes AD 2002–21–08,
Amendment 39–12914.
Applicability
(c) This AD affects the following 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 and serial numbers that
are certificated in any category:
(1) Group 1 (maintains the actions from AD
2002–21–08): All manufacturer serial
numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.
Note: These airplanes are also identified as
Fairchild Republic Company PC–6 airplanes,
Fairchild Heli Porter PC–6 airplanes, or
Fairchild-Hiller Corporation PC–6 airplanes.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Switzerland that requires the actions of AD
2002–21–08 for the added MSN 2001 through
2092 for all the models of the PC–6 airplanes
listed in the type certificate data sheet of
Type Certificate (TC) No. 7A15. We are
issuing this AD to correct improper aileron
assembly configuration, which could result
in failure of the aileron mass balance weight.
Such failure could lead to loss of control of
the airplane.
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect the aileron assembly for proper configuration.
(i) For Group 1 Airplanes: Within the next 30
days after December 6, 2002 (the effective
date of AD 2002–21–08), unless already
done.
(ii) For Group 2 Airplanes: Within the next 30
days after August 7, 2006 (the effective
date of this AD), unless already done.
For All Airplanes: Before further flight after the
inspection required in paragraph (e)(1) of
this AD, unless already done.
Follow Pilatus Service Bulletin No. 62B, dated
May 1967, as specified in Pilatus PC–6
Service Bulletin No. 57–001, dated December 20, 2001.
For All Airplanes: Before further flight after the
inspection required in paragraph (e)(1) of
this AD, unless already done.
Follow Pilatus PC–6 Service Bulletin No. 57–
001, dated December 20, 2001.
(2) If the aileron assembly configuration incorporates
aileron
part
number
(P/N)
6106.10.xxx or P/N 6106.0010.xxx, modify
the assembly following Pilatus Service Bulletin No. 62B, dated May 1967, and install a
placard.
(3) If the aileron assembly configuration differs
from that specified in Pilatus Service Bulletin
No. 62B, dated May 1967, or if the part numbers are missing and cannot be verified:
(i) Obtain a repair scheme from the manufacturer through the FAA at the address
specified in paragraph (f) of this AD; and
(ii) Incorporate this repair scheme.
(4) Do not install any aileron assembly unless
the inspection, modification, placard, and repair requirements (as applicable) of paragraphs (e)(1), (e)(2), (e)(3), (e)(3)(i), and
(e)(3)(ii) of this AD are done.
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Alternative Methods of Compliance
(AMOCs)
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17:57 Jun 21, 2006
Jkt 208001
(i) For Group 1 Airplanes: As of December 6, Follow Pilatus PC–6 Service Bulletin No. 57–
2002 (the effective date of AD 2002–21–08).
001, dated December 20, 2001.
(ii) For Group 2 Airplanes: As of August 7,
2006 (the effective date of this AD)..
Related Information
(f) The Manager, Standards Office, ATTN:
Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; facsimile: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2002–21–08
are approved for this AD.
Follow Pilatus Service Bulletin No. 62B, dated
May 1967, as specified in Pilatus PC–6
Service Bulletin No. 57–001, dated December 20, 2001.
(h) Swiss Airworthiness Directive Number
HB 2005–289, effective date August 23, 2005,
also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must do the actions required by this
AD following the instructions in Pilatus
Service Bulletin No. 62B, dated May 1967,
and Pilatus Service Bulletin No. 57–001,
dated December 20, 2001.
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Sfmt 4700
(1) As of December 6, 2002 (67 FR 64520,
October 21, 2002), the Director of the Federal
Register previously approved the
incorporation by reference of Pilatus Service
Bulletin No. 62B, dated May 1967, and
Pilatus Service Bulletin No. 57–001, dated
December 20, 2001, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
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Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Rules and Regulations
(2) To get a copy of this service
information, contact Pilatus Aircraft Ltd.,
Customer Liaison Manager, CH–6371 Stans,
Switzerland; telephone: +41 41 619 63 19;
facsimile: +41 41 619 6224. 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–
2006–24090; Directorate Identifier 2006–CE–
16–AD.
Issued in Kansas City, Missouri, on June
13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–5587 Filed 6–21–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25102; Directorate
Identifier 2006–NM–117–AD; Amendment
39–14666; AD 2006–13–13]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
mstockstill on PROD1PC68 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Boeing Model 737 airplanes. This AD
requires revising the airplane flight
manual to advise the flightcrew of
improved procedures for pre-flight
setup of the cabin pressurization
system, as well as improved procedures
for interpreting and responding to the
cabin altitude/configuration warning
horn. This AD results from reports that
airplanes have failed to pressurize, and
that the flightcrews failed to react
properly to the cabin altitude warning
horn. We are issuing this AD to prevent
failure of the airplane to pressurize and
subsequent failure of the flightcrew to
recognize and react to a valid cabin
altitude warning horn, which could
result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body)
and consequent loss of airplane control.
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17:57 Jun 21, 2006
Jkt 208001
This AD becomes effective July
7, 2006.
We must receive comments on this
AD by August 21, 2006.
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.
• 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.
FOR FURTHER INFORMATION CONTACT:
Gregg Nesemeier, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6479; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
We have received a report indicating
that during the investigation by the Air
Accident Investigation and Aviation
Safety Board of Greece into the August
14, 2005, Helios Airways accident near
Athens, Greece, it was found that the
Boeing Model 737–300 series airplane
was not pressurized during the climb
from the departure airport, and the
flightcrew subsequently became
incapacitated. It appears that the
pressurization mode selector was
improperly set for flight, and that the
flightcrew subsequently misinterpreted
the cabin altitude warning horn as a
takeoff configuration warning horn. This
misinterpretation may have occurred
because the same warning horn
provides both warning functions on
Model 737 airplanes.
In addition, the FAA has become
aware of a number of other incidents
involving Model 737 airplanes where
the flightcrew reaction to a valid cabin
altitude warning horn was delayed,
either because the flightcrew
misinterpreted the horn as a takeoff
configuration warning horn, or because
they did not immediately don their
oxygen masks. Crew reaction may have
been delayed because the cabin altitude
warning system on Model 737 airplanes
provides only the warning horn; no
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35781
associated cabin altitude warning light
is installed that activates concurrently
with the warning horn.
Failure of the airplane to pressurize
and subsequent failure of the flightcrew
to recognize and react to a valid cabin
altitude warning horn, if not corrected,
could result in incapacitation of the
flightcrew due to hypoxia (lack of
oxygen in body) and consequent loss of
airplane control.
Related Rulemaking
We have previously issued two ADs
to address similar unsafe conditions.
On December 22, 2003, we issued AD
2003–03–15 R1, amendment 39–13366
(68 FR 64802, November 17, 2003), to
require revising the AFM to advise the
flightcrew to don oxygen masks as a first
and immediate step when the cabin
altitude warning occurs. That AD is
applicable to various Boeing and
McDonnell Douglas transport category
airplanes, including Boeing Model 737–
100, –200, –200C, –300, –400, and –500
series airplanes.
On July 14, 2003, we issued AD 2003–
14–08, amendment 39–13227 (68 FR
41519, July 7, 2003), to require revising
the AFM to require the same actions on
various Boeing transport category
airplanes, including Boeing 737–600,
–700, –700C, –800, and –900 series
airplanes.
In paragraph (a) of those ADs, a part
of the revised text that we required to
be placed in the AFMs of Model 737
airplanes reads ‘‘If the cabin altitude
warning horn sounds: * * *’’ or
‘‘Condition: The cabin altitude warning
horn sounds: * * *’’, as applicable.
Boeing has advised us that in light of
the information given in the Discussion
section above, it has updated the AFM
phrase to read ‘‘If the intermittent cabin
altitude/configuration warning horn
sounds in flight: * * *’’ We have
approved this new phrase in the AD as
acceptable for compliance with the
requirements of paragraph (a) of ADs
2003–14–08 and 2003–03–15 R1.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. For this reason, we are issuing
this AD to prevent failure of the airplane
to pressurize and subsequent failure of
the flightcrew to recognize and react to
a valid cabin altitude warning horn,
which could result in incapacitation of
the flightcrew due to hypoxia (lack of
oxygen in body) and consequent loss of
airplane control. This AD requires
revising the airplane flight manual
(AFM) to advise the flightcrew of
E:\FR\FM\22JNR1.SGM
22JNR1
]]>Agencies
[Federal Register Volume 71, Number 120 (Thursday, June 22, 2006)]
[Rules and Regulations]
[Pages 35778-35781]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5587]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24090; Directorate Identifier 2006-CE-16-AD;
Amendment 39-14664; AD 2006-13-11]
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), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 2002-21-08, which applies to certain Pilatus Aircraft Ltd
(Pilatus) Model PC-6 airplanes. AD 2002-21-08 currently requires you to
inspect the aileron assembly for correct
[[Page 35779]]
configuration and modify as necessary. Since we issued AD 2002-21-08,
the FAA determined the action should also apply to all the models of
the PC-6 airplanes listed in the type certificate data sheet of Type
Certificate (TC) No. 7A15 that were produced in the United States
through a licensing agreement between Pilatus and Fairchild Republic
Company (also identified as Fairchild Industries, Fairchild Heli
Porter, or Fairchild-Hiller Corporation). In addition, the intent of
the applicability of AD 2002-21-08 was to apply to all the affected
serial numbers of the airplane models listed in TC No. 7A15. This AD
retains all the actions of AD 2002-21-08, adds those Fairchild Republic
Company airplanes to the applicability of this AD, and lists the
individual specific airplane models. We are issuing this AD to correct
improper aileron assembly configuration, which could result in failure
of the aileron mass balance weight. Such failure could lead to loss of
control of the airplane.
DATES: This AD becomes effective on August 7, 2006.
As of December 6, 2002 (67 FR 64520, October 21, 2002), the
Director of the Federal Register previously approved the incorporation
by reference of Pilatus Service Bulletin No. 62B, dated May 1967, and
Pilatus Service Bulletin No. 57-001, dated December 20, 2001, in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
ADDRESSES: For service information identified in this AD, contact
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-24090; Directorate
Identifier 2006-CE-16-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
On April 17, 2006, 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 the models of the PC-6 airplanes listed in the type
certificate data sheet of TC No. 7A15 that are produced in the United
States through a licensing agreement between Pilatus and Fairchild
Republic Company (also identified as Fairchild Industries, Fairchild
Heli Porter, or Fairchild-Hiller Corporation) airplanes. This proposal
was published in the Federal Register as a notice of proposed
rulemaking (NPRM) on April 21, 2006 (71 FR 20597). The NPRM proposed to
supersede AD 2002-21-08, Amendment 39-12914 (67 FR 64520, October 21,
2002), add those Fairchild Republic Company airplanes to the
applicability of this proposed AD, and list the individual specific
airplane models. The NPRM proposed to retain all the actions of AD
2002-21-08 for inspecting and modifying the aileron assembly.
Comments
We provided the public the opportunity to participate in developing
this AD. We received one comment in favor of the proposed AD.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
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.
Costs of Compliance
We estimate that this AD affects 49 airplanes in the U.S. registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on U.S.
Labor cost Parts cost airplane operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80. Not Applicable................. $80 49 x $80 = $3,920.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary modifications
that would be required based on the results of the inspection. We have
no way of determining the number of airplanes that may need such
modification:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
16 work-hours x $80 per hour = $1,280....... $419 $1,280 + $419 = $1,699.
----------------------------------------------------------------------------------------------------------------
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 AD.
Regulatory Findings
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.
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
[[Page 35780]]
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-2006-24090; Directorate Identifier 2006-CE-16-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 removing Airworthiness Directive (AD)
2002-21-08, Amendment 39-12914 (67 FR 64520, October 21, 2002), and by
adding the following new AD:
2006-13-11 Pilatus Aircraft Ltd.: Amendment 39-14664; Docket No.
FAA-2006-24090; Directorate Identifier 2006-CE-16-AD.
Effective Date
(a) This AD becomes effective on August 7, 2006.
Affected ADs
(b) This AD supersedes AD 2002-21-08, Amendment 39-12914.
Applicability
(c) This AD affects the following 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 and serial numbers that are certificated in any
category:
(1) Group 1 (maintains the actions from AD 2002-21-08): All
manufacturer serial numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.
Note: These airplanes are also identified as Fairchild Republic
Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or
Fairchild-Hiller Corporation PC-6 airplanes.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland that requires the actions of AD 2002-21-08 for the added
MSN 2001 through 2092 for all the models of the PC-6 airplanes
listed in the type certificate data sheet of Type Certificate (TC)
No. 7A15. We are issuing this AD to correct improper aileron
assembly configuration, which could result in failure of the aileron
mass balance weight. Such failure could lead to loss of control of
the airplane.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the aileron (i) For Group 1 Follow Pilatus
assembly for proper Airplanes: Within Service Bulletin
configuration. the next 30 days No. 62B, dated May
after December 6, 1967, as specified
2002 (the effective in Pilatus PC-6
date of AD 2002-21- Service Bulletin
08), unless already No. 57-001, dated
done. December 20, 2001.
(ii) For Group 2
Airplanes: Within
the next 30 days
after August 7,
2006 (the effective
date of this AD),
unless already
done..
(2) If the aileron assembly For All Airplanes: Follow Pilatus
configuration incorporates Before further Service Bulletin
aileron part number (P/N) flight after the No. 62B, dated May
6106.10.xxx or P/N inspection required 1967, as specified
6106.0010.xxx, modify the in paragraph (e)(1) in Pilatus PC-6
assembly following Pilatus of this AD, unless Service Bulletin
Service Bulletin No. 62B, already done. No. 57-001, dated
dated May 1967, and install December 20, 2001.
a placard.
(3) If the aileron assembly For All Airplanes: Follow Pilatus PC-6
configuration differs from Before further Service Bulletin
that specified in Pilatus flight after the No. 57-001, dated
Service Bulletin No. 62B, inspection required December 20, 2001.
dated May 1967, or if the in paragraph (e)(1)
part numbers are missing of this AD, unless
and cannot be verified: already done.
(i) Obtain a repair
scheme from the
manufacturer through
the FAA at the address
specified in paragraph
(f) of this AD; and
(ii) Incorporate this
repair scheme.
(4) Do not install any (i) For Group 1 Follow Pilatus PC-6
aileron assembly unless the Airplanes: As of Service Bulletin
inspection, modification, December 6, 2002 No. 57-001, dated
placard, and repair (the effective date December 20, 2001.
requirements (as of AD 2002-21-08).
applicable) of paragraphs (ii) For Group 2
(e)(1), (e)(2), (e)(3), Airplanes: As of
(e)(3)(i), and (e)(3)(ii) August 7, 2006 (the
of this AD are done. effective date of
this AD)..
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2002-21-08 are approved for this AD.
Related Information
(h) Swiss Airworthiness Directive Number HB 2005-289, effective
date August 23, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must do the actions required by this AD following the
instructions in Pilatus Service Bulletin No. 62B, dated May 1967,
and Pilatus Service Bulletin No. 57-001, dated December 20, 2001.
(1) As of December 6, 2002 (67 FR 64520, October 21, 2002), the
Director of the Federal Register previously approved the
incorporation by reference of Pilatus Service Bulletin No. 62B,
dated May 1967, and Pilatus Service Bulletin No. 57-001, dated
December 20, 2001, in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.
[[Page 35781]]
(2) To get a copy of this service information, contact Pilatus
Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland;
telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. 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-2006-
24090; Directorate Identifier 2006-CE-16-AD.
Issued in Kansas City, Missouri, on June 13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5587 Filed 6-21-06; 8:45 am]
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