Airworthiness Directives; Raytheon Aircraft Company (The Beech Aircraft Company and BEECH Previously Held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777) Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33, 35-C33A, E33A, F33A, E33C, F33C, 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A45 (T-34A, B45), D45 (T-34B), 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B (T-42A), 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 95, B95, B95A, D95A, and E95 Airplanes, 71494-71497 [E6-20970]
Download as PDF
<![CDATA[
71494
Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Actions Accomplished in Accordance With
Previous Revision of Service Bulletin
(g) Actions done before the effective date
of this AD in accordance with Bombardier
Service Bulletin 8–24–83, dated December
23, 2004, are acceptable for compliance with
the corresponding requirements in paragraph
(f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(i) Canadian airworthiness directive CF–
2006–15, dated June 14, 2006, also addresses
the subject of this AD.
Issued in Renton, Washington, on
December 1, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–20969 Filed 12–8–06; 8:45 am]
mstockstill on PROD1PC61 with PROPOSALS
BILLING CODE 4910–13–P
VerDate Aug<31>2005
14:58 Dec 08, 2006
Jkt 211001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26075;
Directorate Identifier 2006–CE–55–AD]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company (The Beech Aircraft
Company and BEECH Previously Held
Type Certificate Nos. 3A15, 3A16, 5A3,
and A–777) Models 35–33, 35–A33, 35–
B33, 35–C33, E33, F33, G33, 35–C33A,
E33A, F33A, E33C, F33C, 35, A35, B35,
C35, D35, E35, F35, G35, H35, J35, K35,
M35, N35, P35, S35, V35, V35A, V35B,
36, A36, A45 (T–34A, B45), D45 (T–
34B), 95–55, 95–A55, 95–B55, 95–B55A,
95–B55B (T–42A), 95–C55, 95–C55A,
D55, D55A, E55, E55A, 56TC, A56TC,
58, 95, B95, B95A, D95A, and E95
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 72–22–01,
which applies to certain Raytheon
Aircraft Company (RAC) (The Beech
Aircraft Company and BEECH
previously held Type Certificate Nos.
3A15, 3A16, 5A3, and A–777) Models
33, 35, 36, 45, and 95 series airplanes.
AD 72–22–01 currently requires you to
determine if each uplock roller is of the
greasible type (one having a drilled and
grooved inner race), replace any
nongreasible uplock roller (one having a
solid inner race) with the greasible type
before further flight, install hollow zerkended mounting bolts on the uplock
rollers, and repetitively lubricate the
uplock mechanism. Since we issued AD
72–22–01, there was a recent incident
involving a RAC Model 95–B55B (T–
42A) airplane where a seizure of the
uplock rollers occurred. This
malfunction of the uplock rollers is
addressed in AD 72–22–01. Thus, the
FAA has determined that the actions of
AD 72–22–01 should also apply to
certain serial numbers of the Model 95–
B55B (T–42A) airplanes. Consequently,
this proposed AD would retain all the
actions of AD 72–22–01, would add
those Model 95–B55B (T–42A) airplanes
to the applicability of this proposed AD,
and would list out the specific serial
numbers. We are proposing this AD to
decrease the possibility of gear-up
landings caused by seizure of the uplock
rollers.
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Sfmt 4702
We must receive comments on
this proposed AD by February 9, 2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Raytheon
Aircraft Company, P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800)
429–5372 or (316) 676–3140.
FOR FURTHER INFORMATION CONTACT:
Anthony Flores, Aerospace Engineer,
Aerospace Engineer, FAA, Wichita
Aircraft Certification Office, 1801
Airport Road, Wichita, Kansas 67209;
telephone: (316) 946–4174; facsimile:
(316) 946–4107.
SUPPLEMENTARY INFORMATION:
DATES:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2006–26075; Directorate
Identifier 2006–CE–55–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
Reports of RAC 33, 35, 36, 45, and 95
series airplanes equipped with nongreasible uplock rollers having a solid
inner race that renders lubrication of the
uplock roller mechanism ineffective
E:\FR\FM\11DEP1.SGM
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Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules
caused us to issue AD 72–22–01,
Amendment 39–1544 (37 FR 22371,
October 19, 1972). AD 72–22–01
currently requires the following on
certain RAC 33, 35, 36, 45, and 95 series
airplanes:
• Determining if each uplock roller is
of the greasible type (one having a
drilled and grooved inner race);
• Replacing any nongreasible uplock
roller (one having a solid inner race)
with the greasible type before further
flight;
• Installing a hollow zerk-ended
mounting bolts on the uplock rollers;
and
• Repetitively lubricating the uplock
mechanism.
Since we issued AD 72–22–01, there
was a recent incident involving a RAC
Model 95–B55B (T–42A) airplane where
a seizure of the uplock rollers occurred.
The design of the uplock rollers is the
same as those uplock rollers on the
airplanes addressed by AD 72–22–01.
This condition, if not corrected, could
result in a gear-up landing.
Relevant Service Information
We have reviewed Beechcraft Service
Instructions No. 0448–211, Rev. I, and
Beechcraft Service Instructions No.
0448–211.
The service information describes
procedures for:
• Determining if each uplock roller is
of the greasible type (one having a
drilled and grooved inner race);
• Replacing any nongreasible uplock
roller (one having a solid inner race)
with the greasible type before further
flight;
• Installing a hollow zerk-ended
mounting bolts on the uplock rollers;
and
• Repetitively lubricating the uplock
mechanism.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
supersede AD 72–22–01 with a new AD
that would retain all the actions of AD
71495
72–22–01, would add those Model 95–
B55B (T–42A) airplanes to the
applicability of this proposed AD, and
would list out the specific serial
numbers. This proposed AD would
require you to use the service
information described previously to
perform these actions.
Costs of Compliance
We estimate that this proposed AD
would affect 9,714 airplanes in the U.S.
registry.
The differences in costs between this
proposed AD and AD 72–22–01 are the
costs associated with the number of
Model 95–B55B (T–42A) airplanes that
were not affected by AD 72–22–01.
We estimate the following costs to do
the proposed actions to determine if
each uplock roller is of the greasible
type (one having a drilled and grooved
inner race), replace any nongreasible
uplock roller (one having a solid inner
race) with the greasible type before
further flight, install hollow zerk-ended
mounting bolts on the uplock rollers,
and initially lubricate the uplock
mechanism:
Labor cost
Parts cost
Total cost
per
airplane
Total cost
on U.S.
operators
2 work-hours × $80 per hour = $160 ........................................................................................................
$30
$190
$1,845,660
Labor cost
Parts cost
Total cost
per
airplane
Total cost
on U.S.
operators
1 work-hour × $80 per hour = $80 ............................................................................................................
None
$80
$777,120
We estimate the following costs for
each lubrication of the uplock
mechanism.
mstockstill on PROD1PC61 with PROPOSALS
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
VerDate Aug<31>2005
14:58 Dec 08, 2006
Jkt 211001
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Fmt 4702
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2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
E:\FR\FM\11DEP1.SGM
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71496
Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules
Identifier 2006–CE–55–AD; Supersedes
AD 72–22–01; Amendment 39–1544.
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
PART 39—AIRWORTHINESS
DIRECTIVES
List of Subjects in 14 CFR Part 39
§ 39.13
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
72–22–01, Amendment 39–1544, and
adding the following new AD:
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Raytheon Aircraft Company (The Beech
Aircraft Company and BEECH
previously held Type Certificate Nos.
3A15, 3A16, 5A3, and A–777): Docket
No. FAA–2006–26075; Directorate
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by
February 9, 2007.
Affected ADs
(b) This AD supersedes AD 72–22–01,
Amendment 39–1544.
Unsafe Condition
(c) This AD applies to the following
airplane models and serial numbers (SNs)
that are certificated in any category:
(1) Group 1 (maintains the actions from AD
72–22–01):
Model
SNs
(i) 35–33, 35–A33, 35–B33, 35–C33, E33, F33, and G33 ............................................................................................
(ii) 35–C33A, E33A, and F33A .......................................................................................................................................
(iii) E33C and F33C ........................................................................................................................................................
(iv) 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B ...............
(v) 36 and A36 ................................................................................................................................................................
(vi) A45 (T–34A, B45) and D45 (T–34B) .......................................................................................................................
(vii) 95–55, 95–A55, 95–B55, and 95–B55A ..................................................................................................................
(viii) 95–C55, 95–C55A, D55, D55A, E55, and E55A ....................................................................................................
(ix) 56TC and A56TC .....................................................................................................................................................
(x) 58 ...............................................................................................................................................................................
(xi) 95, B95, B95A, D95A, and E95 ...............................................................................................................................
(2) Group 2: Model 95-B55B (T–42A)
airplanes, SNs TF–1 through TF–70.
Unsafe Condition
(d) This AD results from a recent incident
involving a Raytheon Aircraft Company
(RAC) Model 95–B55B (T–42A) airplane
where a seizure of the uplock rollers
occurred. We are issuing this AD to decrease
the possibility of gear-up landings caused by
seizure of the uplock rollers.
CD–1 through CD–1256.
CE–1 through CE–349.
CJ–1 through CJ–30.
D–1 through D–9287.
E1 through E–283.
All.
TC–1 through TC–1402.
TE–1 through TE–846.
TG–1 through TG–94.
TH–1 through TH–174.
TD–2 through TD–721.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Determine if each uplock roller is of the
greasible type (one having a drilled and
grooved inner race).
(A) For Group 1 airplanes: Within 300 hours
time-in-service (TIS) after October 25, 1972
(the effective date of AD 72–22–01).
(B) For Group 2 airplanes: Within 300 hours
TIS after the effective date of this AD.
(A) For Group 1 airplanes: Before further flight
after the determination required by paragraph (e)(1)(A) of this AD.
(B) For Group 2 airplanes: Before further flight
after the determination required by paragraph (e)(1)(B) of this AD.
(A) For Group 1 airplanes: Within 300 hours
TIS after October 25, 1972 (the effective
date of AD 72–22–01).
(B) For Group 2 airplanes: Within 300 hours
TIS after the effective date of this AD.
(A) For Group 1 airplanes: Initially within 300
hours TIS after October 25, 1972 (the effective date of AD 72–22–01). Repetitively lubricate thereafter at intervals not to exceed
100 hours TIS.
(B) For Group 2 airplanes: Initially within 300
hours TIS after the effective date of this
AD. Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS.
Follow Beechcraft Service Instructions No.
0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211.
(2) Replace any nongreasible uplock roller (one
having a solid inner race) with the greasible
type.
(3) Install hollow zerk-ended mounting bolts on
the uplock rollers.
mstockstill on PROD1PC61 with PROPOSALS
(4) Lubricate the uplock mechanism ..................
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Wichita Aircraft
Certification Office, FAA, ATTN: Anthony
VerDate Aug<31>2005
14:58 Dec 08, 2006
Jkt 211001
Flores, Aerospace Engineer, 1801 Airport
Road, Wichita, Kansas 67209; telephone:
(316) 946–4174; facsimile: (316) 946–4107,
has the authority to approve AMOCs for this
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Follow Beechcraft Service Instructions No.
0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211.
Follow Beechcraft Service Instructions No.
0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211.
Follow Beechcraft Service Instructions No.
0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211.
AD, if requested using the procedures found
in 14 CFR 39.19.
(g) AMOCs approved for AD 72–22–01 are
approved for this AD.
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Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules
Related Information
(h) To get copies of the service information
referenced in this AD, contact Raytheon
Aircraft Company, P.O. Box 85, Wichita,
Kansas 67201–0085; telephone: (800) 429–
5372 or (316) 676–3140. To view the AD
docket, go to the Docket Management
Facility; U.S. Department of Transportation,
400 Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC, or on the
Internet at https://dms.dot.gov. The docket
number is Docket No. FAA–2006–26075;
Directorate Identifier 2006–CE–55–AD.
Issued in Kansas City, Missouri, on
December 4, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–20970 Filed 12–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26371; Directorate
Identifier 2006–CE–70–AD]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Limited PC–12 and PC–12/45
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
mstockstill on PROD1PC61 with PROPOSALS
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as executive seats equipped
with pedestal legs that were produced
using a material that deviates from the
approved design data. The proposed AD
would require actions that are intended
to address the unsafe condition
described in the MCAI.
DATES: We must receive comments on
this proposed AD by January 10, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
VerDate Aug<31>2005
14:58 Dec 08, 2006
Jkt 211001
71497
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer, 901
Locust, Room 301; telephone (816) 329–
4059; fax (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
The Federal Office of Civil Aviation
(FOCA), which is the aviation authority
for Switzerland, has issued FOCA AD
HB–2006–444, dated November 7, 2006
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states
that executive seats equipped with
pedestal legs were produced using a
material that deviates from the approved
design data. As a consequence the
pedestal legs may not perform as
intended under emergency landing
conditions. In order to correct and
control the situation, this AD requires a
one time inspection to identify the
Vendor Part Number (VPN) of the
pedestal legs and the Serial Number
(S/N) of the executive seat and the
replacement of the pedestal legs if
necessary. You may obtain further
information by examining the MCAI in
the AD docket.
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–26371; Directorate Identifier
2006–CE–70–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
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Fmt 4702
Sfmt 4702
Relevant Service Information
Pilatus Aircraft Limited has issued
Service Bulletin No.: 25–032, dated
October 2, 2006, and DeCrane Aircraft
Seating Company, Inc. has issued
Mandatory Service Bulletin SB05147
Revision B, dated June 26, 2006. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of the Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
E:\FR\FM\11DEP1.SGM
11DEP1
]]>Agencies
[Federal Register Volume 71, Number 237 (Monday, December 11, 2006)]
[Proposed Rules]
[Pages 71494-71497]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20970]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company (The Beech
Aircraft Company and BEECH Previously Held Type Certificate Nos. 3A15,
3A16, 5A3, and A-777) Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33,
G33, 35-C33A, E33A, F33A, E33C, F33C, 35, A35, B35, C35, D35, E35, F35,
G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A45
(T-34A, B45), D45 (T-34B), 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B (T-
42A), 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 95, B95,
B95A, D95A, and E95 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 72-22-01,
which applies to certain Raytheon Aircraft Company (RAC) (The Beech
Aircraft Company and BEECH previously held Type Certificate Nos. 3A15,
3A16, 5A3, and A-777) Models 33, 35, 36, 45, and 95 series airplanes.
AD 72-22-01 currently requires you to determine if each uplock roller
is of the greasible type (one having a drilled and grooved inner race),
replace any nongreasible uplock roller (one having a solid inner race)
with the greasible type before further flight, install hollow zerk-
ended mounting bolts on the uplock rollers, and repetitively lubricate
the uplock mechanism. Since we issued AD 72-22-01, there was a recent
incident involving a RAC Model 95-B55B (T-42A) airplane where a seizure
of the uplock rollers occurred. This malfunction of the uplock rollers
is addressed in AD 72-22-01. Thus, the FAA has determined that the
actions of AD 72-22-01 should also apply to certain serial numbers of
the Model 95-B55B (T-42A) airplanes. Consequently, this proposed AD
would retain all the actions of AD 72-22-01, would add those Model 95-
B55B (T-42A) airplanes to the applicability of this proposed AD, and
would list out the specific serial numbers. We are proposing this AD to
decrease the possibility of gear-up landings caused by seizure of the
uplock rollers.
DATES: We must receive comments on this proposed AD by February 9,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone: (800) 429-5372 or (316) 676-3140.
FOR FURTHER INFORMATION CONTACT: Anthony Flores, Aerospace Engineer,
Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801
Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4174;
facsimile: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-26075; Directorate Identifier 2006-CE-55-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.
Discussion
Reports of RAC 33, 35, 36, 45, and 95 series airplanes equipped
with non-greasible uplock rollers having a solid inner race that
renders lubrication of the uplock roller mechanism ineffective
[[Page 71495]]
caused us to issue AD 72-22-01, Amendment 39-1544 (37 FR 22371, October
19, 1972). AD 72-22-01 currently requires the following on certain RAC
33, 35, 36, 45, and 95 series airplanes:
Determining if each uplock roller is of the greasible type
(one having a drilled and grooved inner race);
Replacing any nongreasible uplock roller (one having a
solid inner race) with the greasible type before further flight;
Installing a hollow zerk-ended mounting bolts on the
uplock rollers; and
Repetitively lubricating the uplock mechanism.
Since we issued AD 72-22-01, there was a recent incident involving
a RAC Model 95-B55B (T-42A) airplane where a seizure of the uplock
rollers occurred. The design of the uplock rollers is the same as those
uplock rollers on the airplanes addressed by AD 72-22-01.
This condition, if not corrected, could result in a gear-up
landing.
Relevant Service Information
We have reviewed Beechcraft Service Instructions No. 0448-211, Rev.
I, and Beechcraft Service Instructions No. 0448-211.
The service information describes procedures for:
Determining if each uplock roller is of the greasible type
(one having a drilled and grooved inner race);
Replacing any nongreasible uplock roller (one having a
solid inner race) with the greasible type before further flight;
Installing a hollow zerk-ended mounting bolts on the
uplock rollers; and
Repetitively lubricating the uplock mechanism.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would supersede AD 72-22-01 with a new AD that would retain all the
actions of AD 72-22-01, would add those Model 95-B55B (T-42A) airplanes
to the applicability of this proposed AD, and would list out the
specific serial numbers. This proposed AD would require you to use the
service information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would affect 9,714 airplanes in
the U.S. registry.
The differences in costs between this proposed AD and AD 72-22-01
are the costs associated with the number of Model 95-B55B (T-42A)
airplanes that were not affected by AD 72-22-01.
We estimate the following costs to do the proposed actions to
determine if each uplock roller is of the greasible type (one having a
drilled and grooved inner race), replace any nongreasible uplock roller
(one having a solid inner race) with the greasible type before further
flight, install hollow zerk-ended mounting bolts on the uplock rollers,
and initially lubricate the uplock mechanism:
------------------------------------------------------------------------
Total cost Total cost on
Labor cost Parts cost per U.S.
airplane operators
------------------------------------------------------------------------
2 work-hours x $80 per hour = $30 $190 $1,845,660
$160.........................
------------------------------------------------------------------------
We estimate the following costs for each lubrication of the uplock
mechanism.
------------------------------------------------------------------------
Total cost Total cost on
Labor cost Parts cost per U.S.
airplane operators
------------------------------------------------------------------------
1 work-hour x $80 per hour = None $80 $777,120
$80..........................
------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m.,
[[Page 71496]]
Monday through Friday, except Federal holidays. The Docket Office
(telephone (800) 647-5227) is located at the street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 72-22-01, Amendment 39-1544, and adding the following new AD:
Raytheon Aircraft Company (The Beech Aircraft Company and BEECH
previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777):
Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD;
Supersedes AD 72-22-01; Amendment 39-1544.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by February 9, 2007.
Affected ADs
(b) This AD supersedes AD 72-22-01, Amendment 39-1544.
Unsafe Condition
(c) This AD applies to the following airplane models and serial
numbers (SNs) that are certificated in any category:
(1) Group 1 (maintains the actions from AD 72-22-01):
------------------------------------------------------------------------
Model SNs
------------------------------------------------------------------------
(i) 35-33, 35-A33, 35-B33, 35-C33, CD-1 through CD-1256.
E33, F33, and G33.
(ii) 35-C33A, E33A, and F33A...... CE-1 through CE-349.
(iii) E33C and F33C............... CJ-1 through CJ-30.
(iv) 35, A35, B35, C35, D35, E35, D-1 through D-9287.
F35, G35, H35, J35, K35, M35,
N35, P35, S35, V35, V35A, and
V35B.
(v) 36 and A36.................... E1 through E-283.
(vi) A45 (T-34A, B45) and D45 (T- All.
34B).
(vii) 95-55, 95-A55, 95-B55, and TC-1 through TC-1402.
95-B55A.
(viii) 95-C55, 95-C55A, D55, D55A, TE-1 through TE-846.
E55, and E55A.
(ix) 56TC and A56TC............... TG-1 through TG-94.
(x) 58............................ TH-1 through TH-174.
(xi) 95, B95, B95A, D95A, and E95. TD-2 through TD-721.
------------------------------------------------------------------------
(2) Group 2: Model 95-B55B (T-42A) airplanes, SNs TF-1 through
TF-70.
Unsafe Condition
(d) This AD results from a recent incident involving a Raytheon
Aircraft Company (RAC) Model 95-B55B (T-42A) airplane where a
seizure of the uplock rollers occurred. We are issuing this AD to
decrease the possibility of gear-up landings caused by seizure of
the uplock rollers.
Compliance
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Determine if each uplock (A) For Group 1 Follow Beechcraft
roller is of the greasible airplanes: Within Service
type (one having a drilled 300 hours time-in- Instructions No.
and grooved inner race). service (TIS) after 0448-211, Rev. I,
October 25, 1972 or Beechcraft
(the effective date Service
of AD 72-22-01). Instructions No.
0448-211.
(B) For Group 2
airplanes: Within
300 hours TIS after
the effective date
of this AD.
(2) Replace any nongreasible (A) For Group 1 Follow Beechcraft
uplock roller (one having a airplanes: Before Service
solid inner race) with the further flight Instructions No.
greasible type. after the 0448-211, Rev. I,
determination or Beechcraft
required by Service
paragraph (e)(1)(A) Instructions No.
of this AD. 0448-211.
(B) For Group 2
airplanes: Before
further flight
after the
determination
required by
paragraph (e)(1)(B)
of this AD.
(3) Install hollow zerk- (A) For Group 1 Follow Beechcraft
ended mounting bolts on the airplanes: Within Service
uplock rollers. 300 hours TIS after Instructions No.
October 25, 1972 0448-211, Rev. I,
(the effective date or Beechcraft
of AD 72-22-01). Service
Instructions No.
0448-211.
(B) For Group 2
airplanes: Within
300 hours TIS after
the effective date
of this AD.
(4) Lubricate the uplock (A) For Group 1 Follow Beechcraft
mechanism. airplanes: Service
Initially within Instructions No.
300 hours TIS after 0448-211, Rev. I,
October 25, 1972 or Beechcraft
(the effective date Service
of AD 72-22-01). Instructions No.
Repetitively 0448-211.
lubricate
thereafter at
intervals not to
exceed 100 hours
TIS.
(B) For Group 2
airplanes:
Initially within
300 hours TIS after
the effective date
of this AD.
Repetitively
lubricate
thereafter at
intervals not to
exceed 100 hours
TIS.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office, FAA,
ATTN: Anthony Flores, Aerospace Engineer, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316) 946-4174; facsimile: (316)
946-4107, 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 72-22-01 are approved for this AD.
[[Page 71497]]
Related Information
(h) To get copies of the service information referenced in this
AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas
67201-0085; telephone: (800) 429-5372 or (316) 676-3140. To view the
AD docket, go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC, or on the Internet at https://dms.dot.gov. The
docket number is Docket No. FAA-2006-26075; Directorate Identifier
2006-CE-55-AD.
Issued in Kansas City, Missouri, on December 4, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-20970 Filed 12-8-06; 8:45 am]
BILLING CODE 4910-13-P
