Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes, 52983-52988 [06-7511]
Download as PDF
<![CDATA[
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
DEPARTMENT OF AGRICULTURE
Animal and Plant Health Inspection
Service
9 CFR Parts 55 and 81
[Docket No. 00–108–4]
Chronic Wasting Disease Herd
Certification Program and Interstate
Movement of Farmed or Captive Deer,
Elk, and Moose; Delay of Effective Date
Animal and Plant Health
Inspection Service, USDA.
ACTION: Final rule; delay of effective
date.
AGENCY:
SUMMARY: We recently amended the
regulations to establish a herd
certification program and interstate
movement restrictions for cervids to
control the spread of chronic wasting
disease. That final rule had an effective
date of October 19, 2006. We are
delaying that effective date until further
notice, to give the agency time to
consider several petitions we recently
received that asked for the rule not to
take effect as scheduled. This delay is
needed to allow the agency to consider
the issues raised in the petitions and
decide what action to take in response
to them.
DATES: The effective date for the final
rule amending 9 CFR part 55 and adding
9 CFR part 81, published at 71 FR
41682, July 21, 2006, is delayed until
further notice. APHIS will publish a
document in the Federal Register
announcing any new effective date or
other decision.
FOR FURTHER INFORMATION CONTACT: Dr.
Dean E. Goeldner, Senior Staff
Veterinarian, Ruminant Health
Programs, VS, APHIS, 4700 River Road
Unit 43, Riverdale, MD 20737–1231;
(301) 734–4916.
SUPPLEMENTARY INFORMATION:
rwilkins on PROD1PC63 with RULES
Background
The Animal and Plant Health
Inspection Service’s (APHIS’s)
regulations in 9 CFR subchapter B
govern cooperative programs to control
and eradicate communicable diseases of
livestock. In accordance with the
Animal Health Protection Act (7 U.S.C.
8301 et seq.), the Secretary of
Agriculture has the authority to issue
orders and promulgate regulations to
prevent the introduction into the United
States and the dissemination within the
United States of any pest or disease of
livestock, and to pay claims growing out
of the destruction of animals.
On July 21, 2006, we published a final
rule in the Federal Register (71 FR
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
41682–41707) amending 9 CFR
subchapter B by establishing regulations
in part 55 for a Chronic Wasting Disease
Herd Certification Program to help
eliminate chronic wasting disease from
the farmed or captive cervid herds in
the United States (the CWD rule). Under
that rule, owners of deer, elk, and moose
herds who choose to participate would
have to follow program requirements for
animal identification, testing, herd
management, and movement of animals
into and from herds. We also amended
9 CFR subchapter B by establishing a
new part 81 containing interstate
movement requirements to prevent the
spread of CWD.
Delay in Effective Date
We recently received several petitions
requesting a delay in the effective date
of the CWD rule and reconsideration of
several requirements of the rule. We are
currently evaluating the merits of these
petitions, and will publish a notice in
the Federal Register in the near future
making the contents of the petitions
available to the public for comment. We
are delaying the effective date of the
CWD rule while this process is
underway.
Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22,
2.80, and 371.4.
Done in Washington, DC, this 30th day of
August 2006.
W. Ron DeHaven,
Administrator, Animal and Plant Health
Inspection Service.
[FR Doc. E6–14861 Filed 9–7–06; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25760; Directorate
Identifier 2006–CE–48–AD; Amendment 39–
14757; AD 2006–18–51]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company Models 1900, 1900C,
and 1900D Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Raytheon Aircraft Company (RAC)
Models 1900, 1900C, and 1900D
airplanes. This AD contains the same
information as emergency AD 2006–18–
51 and publishes the action in the
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
52983
Federal Register. This AD requires you
to do a one-time visual inspection of
both the left and right wing rear spar
lower caps for cracking and other
damage such as loose or missing
fasteners; repair any cracks or damage
found; and report any cracks or damage
found to the FAA and RAC. This AD
results from extensive cracks found in
the wing rear spar lower caps and rear
spar web of two of the affected
airplanes. One of the airplanes also had
missing fasteners. We are issuing this
AD to detect and correct cracking and
other damage in the wing rear spar
lower caps of the affected airplanes
before the cracks or damage lead to
failure. Such a wing failure could result
in the wing separating from the airplane
with consequent loss of control.
DATES: This AD becomes effective on
September 8, 2006.
We must receive any comments on
this AD by November 7, 2006.
ADDRESSES: Use one of the following
addresses to comment 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–
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.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2006–25760;
Directorate Identifier 2006–CE–48–AD.
FOR FURTHER INFORMATION CONTACT:
Steven E. Potter, FAA, 1801 Airport
Road, Wichita, Kansas 67209;
telephone: (316) 946–4124; fax: (316)
946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA received recent reports of
cracks found in the wings of two RAC
1900D airplanes. During routine
maintenance, the wing rear spar lower
caps and rear spar web were found to
have significant cracks.
The RAC Structural Inspection
Manual requires a thorough inspection
of the wing rear spar at 17,500 hours
time-in-service (TIS) with repetitive
inspections at intervals of 3,000 hours
TIS.
E:\FR\FM\08SER1.SGM
08SER1
52984
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
One airplane had 19,126 hours TIS
when cracks were found. The cracks
were in the lower aft spar cap flange,
but the cracks extended upward into the
web and terminated at the lightening
hole in the spar web. Fasteners were
also found missing in the spar cap and
wing cove splice plate. There were no
discrepancies recorded from the initial
inspection at 17,500 hours TIS on this
airplane.
Early indications show similar
cracking on the other airplane. We
continue to gather information on this
airplane.
Analysis shows that similar cracks
could also develop in the wings of the
Models 1900 and 1900C airplanes.
Cracking in the wing rear spar lower
caps, if not corrected, could result in
wing failure. Such a wing failure could
result in the wing separating from the
airplane with consequent loss of
control.
On August 31, 2006, FAA issued
emergency AD 2006–18–51 to require
you to do a one-time visual inspection
of both the left and right wing rear spar
lower caps for cracking and other
damage such as loose or missing
fasteners; repair any cracks or damage
found; and report any cracks or damage
found to the FAA and RAC.
rwilkins on PROD1PC63 with RULES
FAA’s Determination
The FAA determined that immediate
corrective action was required, that
notice and opportunity for prior public
comment were impracticable and
contrary to the public interest, and that
good cause existed to make the AD
effective immediately by individual
letters issued on August 31, 2006, to all
known U.S. operators of the affected
RAC Models 1900, 1900C, and 1900D
airplanes. These conditions still exist,
and the AD is published in the Federal
Register as an amendment to section
39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it
effective to all persons.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and an
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments regarding this
AD. Send your comments to an address
listed under the ADDRESSES section.
Include the docket number ‘‘FAA–
2006–25760; Directorate Identifier
2006–CE–48–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
and may amend the 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 AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the AD, the regulatory
evaluation, any comments received, and
other information on the Internet at
https://dms.dot.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2006–18–51 Raytheon Aircraft Company
(RAC): Amendment 39–14757; Docket
No. FAA–2005–25760; Directorate
Identifier 2006–CE–48–AD.
Effective Date
(a) This AD becomes effective on
September 8, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
Models
Serial Nos.
(1) 1900 .....................
(2) 1900C (C–12J) ....
UA–3.
UB–1 through UB–
74, UC–1 through
UC–174, and UD–
1 through UD–6.
UE–1 through UE–
439.
(3) 1900D ..................
Unsafe Condition
(d) This AD is the result of extensive cracks
found in the wing rear spar lower caps and
rear spar web of two of the affected airplanes.
One of the airplanes also had missing
fasteners. We are issuing this AD to detect
and correct cracking and other damage in the
wing rear spar lower caps of the affected
airplanes before the cracks or damage lead to
failure. Such a wing failure could result in
the wing separating from the airplane with
consequent loss of control.
Compliance
(e) To address this problem, you must do
the following:
E:\FR\FM\08SER1.SGM
08SER1
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
52985
Actions
Compliance
Procedures
(1) A one-time visual inspection of both the left
and right wing rear spar lower caps for
cracks and other damage such as loose or
missing fasteners.
At whichever occurs later after September 8,
2006 (the effective date of this AD), except
to those who received emergency AD
2006–18–51, which contained the requirements of this amendment and became effective immediately upon receipt:
(i) Within 24 hours; or
(ii) Prior to further flight.
For this repositioning, you may operate the
airplane up to 3 hours time-in-service provided the flight(s) occur(s) no later than 30
days after September 8, 2006 (the effective
date of this AD), except to those who received emergency AD 2006–18–51, which
contained the requirements of this amendment and became effective immediately
upon receipt.
Follow the procedures in the Appendix to this
AD.
(2) For the inspection in paragraph (e)(1) of this
AD, you may return/position the airplane to a
home base, hangar, maintenance facility, etc.
(3) Repair any cracks or other damage such as
loose or missing fasteners found during the
inspection required in paragraph (e)(1) of this
AD. Do this by obtaining and incorporating an
FAA-approved repair scheme from RAC.
(4) Report the inspection results to the FAA
and RAC. For the reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the
information collection requirements and has
assigned OMB Control Number 2120–0056.
Alternative Methods of Compliance
(AMOCs)
rwilkins on PROD1PC63 with RULES
18:59 Sep 07, 2006
Jkt 208001
Within 72 hours after completing the inspection required in paragraph (e)(1) of this AD.
APPENDIX TO AD 2006–18–51
(f) The Manager, Wichita Aircraft
Certification Office, FAA, ATTN: Steven E.
Potter, FAA, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946–4124;
fax: (316) 946–4107, has the authority to
approve AMOCs for this AD, if requested
using the procedures in 14 CFR 39.
VerDate Aug<31>2005
Before further flight after the inspection required by paragraph (e)(1) of this AD.
Inspection Instructions—Raytheon Aircraft
Company 1900 Series Wing Rear Spar
Step 1. Lower the wing flaps to provide
visual access to the wing rear spar cove area.
Although the pictures show the flaps
removed, this AD does not require flap
removal to do the inspection.
Step 2. Using a strong, high-intensity light
visually inspect the area of the wing rear spar
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
The following limitations are imposed for such
a repositioning flight:
(i) ONLY THE PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION IS
ALLOWED FOR THIS FLIGHT;
(ii) FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED; and
(iii) INDICATED AIRSPEED IS LIMITED
TO 175 KNOTS MAXIMUM.
Contact RAC at Post Office Box 85, Wichita,
Kansas 67201–0085; phone: 316–676–
8366; fax: (316) 676–8745; e-mail:
tom_peay@rac.ray.com.
Send your report to Steven E. Potter, FAA,
1801 Airport Road, Wichita, Kansas 67209;
fax:
(316)
946–4107;
e-mail:
steven.potter@faa.gov;
and
Tom
Peay,
Raytheon Aircraft Company, Post Office
Box 85, Wichita, Kansas 67201–0085; fax:
(316) 676–8745; e-mail: tom_peay@
rac.ray.com. Include in your report the following information:
(i) Aircraft model and serial number;
(ii) Number of cycles;
(iii) Aircraft hours TIS;
(iv) Left and right wing lower spar cap
hours TIS;
(v) Hours TIS on the spar cap since last
inspection;
(vi) Answer yes or no whether cracking,
missing fasteners, or other damage
was found; and
(vii) If cracking was found, identify size
and location of cracks.
identified in Figure 1. There is ample
visually visual access from above the upper
surface of the flap. Look for cracks (like those
shown in Figures 2 and 3) and loose or
missing fasteners.
Step 3. Clean the wing rear spar area 10
inches inboard and outboard of the buttock
line (BL) 114 area.
Step 4. Repeat the Step 2 inspection.
BILLING CODE 4910–13–U
E:\FR\FM\08SER1.SGM
08SER1
VerDate Aug<31>2005
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
17:41 Sep 07, 2006
Jkt 208001
PO 00000
Frm 00006
Fmt 4700
Sfmt 4725
E:\FR\FM\08SER1.SGM
08SER1
ER08SE06.002</GPH>
rwilkins on PROD1PC63 with RULES
52986
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
PO 00000
Frm 00007
Fmt 4700
Sfmt 4725
E:\FR\FM\08SER1.SGM
08SER1
52987
ER08SE06.003</GPH>
rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
Issued in Kansas City, Missouri, on
September 1, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–7511 Filed 9–7–06; 8:45 am]
BILLING CODE 4910–13–C
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25513; Directorate
Identifier 99–NE–61–AD; Amendment 39–
14753; AD 2006–18–14]
rwilkins on PROD1PC63 with RULES
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Tay 650–15
and Tay 651–54 Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
ACTION:
Final rule.
SUMMARY: The FAA is superseding an
airworthiness directive (AD) for RollsRoyce Deutschland Ltd & Co KG (RRD)
Tay 650–15 and Tay 651–54 turbofan
engines. That AD currently establishes
cyclic life limits for certain part number
(P/N) stage 1 high pressure turbine
(HPT) discs and stage 1 low pressure
turbine (LPT) discs operating under
certain flight plan profiles. This AD
requires calculating and re-establishing
the achieved cyclic life of stage 1 HPT
discs, P/N JR32013 or P/N JR33838, and
stage 1 LPT discs, P/N JR32318A, that
have been exposed to different flight
plan profiles. This AD also requires
removing from service those stage 1
HPT discs and stage 1 LPT discs
operated under Tay 650–15 engine flight
plan profiles A, B, C, and D, and
operated under Tay 651–54 engine
datum flight profile, at reduced cyclic
life limits, using a drawdown schedule.
This AD results from RRD updating
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
their low-cycle-fatigue analysis for stage
1 HPT discs and stage 1 LPT discs and
reducing their cyclic life limits. We are
issuing this AD to prevent cracks
leading to turbine disc failure, which
could result in an uncontained engine
failure and damage to the airplane.
This AD becomes effective
October 13, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of October 13, 2006.
DATES:
You can get the service
information identified in this AD from
Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, 15872 BlankenfeldeMahlow, Germany, telephone 49–0–33–
7086–1768; fax 49–0–33–7086–3356.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
ADDRESSES:
E:\FR\FM\08SER1.SGM
08SER1
ER08SE06.004</GPH>
52988
]]>Agencies
[Federal Register Volume 71, Number 174 (Friday, September 8, 2006)]
[Rules and Regulations]
[Pages 52983-52988]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-7511]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25760; Directorate Identifier 2006-CE-48-AD;
Amendment 39-14757; AD 2006-18-51]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Models 1900,
1900C, and 1900D Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D
airplanes. This AD contains the same information as emergency AD 2006-
18-51 and publishes the action in the Federal Register. This AD
requires you to do a one-time visual inspection of both the left and
right wing rear spar lower caps for cracking and other damage such as
loose or missing fasteners; repair any cracks or damage found; and
report any cracks or damage found to the FAA and RAC. This AD results
from extensive cracks found in the wing rear spar lower caps and rear
spar web of two of the affected airplanes. One of the airplanes also
had missing fasteners. We are issuing this AD to detect and correct
cracking and other damage in the wing rear spar lower caps of the
affected airplanes before the cracks or damage lead to failure. Such a
wing failure could result in the wing separating from the airplane with
consequent loss of control.
DATES: This AD becomes effective on September 8, 2006.
We must receive any comments on this AD by November 7, 2006.
ADDRESSES: Use one of the following addresses to comment 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 20590-0001.
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.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2006-25760; Directorate Identifier 2006-CE-48-AD.
FOR FURTHER INFORMATION CONTACT: Steven E. Potter, FAA, 1801 Airport
Road, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-
4107.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA received recent reports of cracks found in the wings of two
RAC 1900D airplanes. During routine maintenance, the wing rear spar
lower caps and rear spar web were found to have significant cracks.
The RAC Structural Inspection Manual requires a thorough inspection
of the wing rear spar at 17,500 hours time-in-service (TIS) with
repetitive inspections at intervals of 3,000 hours TIS.
[[Page 52984]]
One airplane had 19,126 hours TIS when cracks were found. The
cracks were in the lower aft spar cap flange, but the cracks extended
upward into the web and terminated at the lightening hole in the spar
web. Fasteners were also found missing in the spar cap and wing cove
splice plate. There were no discrepancies recorded from the initial
inspection at 17,500 hours TIS on this airplane.
Early indications show similar cracking on the other airplane. We
continue to gather information on this airplane.
Analysis shows that similar cracks could also develop in the wings
of the Models 1900 and 1900C airplanes.
Cracking in the wing rear spar lower caps, if not corrected, could
result in wing failure. Such a wing failure could result in the wing
separating from the airplane with consequent loss of control.
On August 31, 2006, FAA issued emergency AD 2006-18-51 to require
you to do a one-time visual inspection of both the left and right wing
rear spar lower caps for cracking and other damage such as loose or
missing fasteners; repair any cracks or damage found; and report any
cracks or damage found to the FAA and RAC.
FAA's Determination
The FAA determined that immediate corrective action was required,
that notice and opportunity for prior public comment were impracticable
and contrary to the public interest, and that good cause existed to
make the AD effective immediately by individual letters issued on
August 31, 2006, to all known U.S. operators of the affected RAC Models
1900, 1900C, and 1900D airplanes. These conditions still exist, and the
AD is published in the Federal Register as an amendment to section
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it
effective to all persons.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2006-
25760; Directorate Identifier 2006-CE-48-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the 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 AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at https://dms.dot.gov; or in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located at the street address stated in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2006-18-51 Raytheon Aircraft Company (RAC): Amendment 39-14757;
Docket No. FAA-2005-25760; Directorate Identifier 2006-CE-48-AD.
Effective Date
(a) This AD becomes effective on September 8, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Models Serial Nos.
------------------------------------------------------------------------
(1) 1900................................. UA-3.
(2) 1900C (C-12J)........................ UB-1 through UB-74, UC-1
through UC-174, and UD-1
through UD-6.
(3) 1900D................................ UE-1 through UE-439.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD is the result of extensive cracks found in the wing
rear spar lower caps and rear spar web of two of the affected
airplanes. One of the airplanes also had missing fasteners. We are
issuing this AD to detect and correct cracking and other damage in
the wing rear spar lower caps of the affected airplanes before the
cracks or damage lead to failure. Such a wing failure could result
in the wing separating from the airplane with consequent loss of
control.
Compliance
(e) To address this problem, you must do the following:
[[Page 52985]]
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) A one-time visual inspection of At whichever occurs later after Follow the procedures in the
both the left and right wing rear September 8, 2006 (the effective Appendix to this AD.
spar lower caps for cracks and date of this AD), except to those
other damage such as loose or who received emergency AD 2006-18-
missing fasteners. 51, which contained the
requirements of this amendment and
became effective immediately upon
receipt:
(i) Within 24 hours; or
(ii) Prior to further flight.
(2) For the inspection in paragraph For this repositioning, you may The following limitations are
(e)(1) of this AD, you may return/ operate the airplane up to 3 hours imposed for such a repositioning
position the airplane to a home time-in-service provided the flight:
base, hangar, maintenance facility, flight(s) occur(s) no later than 30 (i) ONLY THE PILOT AND ANY
etc. days after September 8, 2006 (the ADDITIONAL FLIGHT CREW MEMBER
effective date of this AD), except REQUIRED FOR SAFE OPERATION IS
to those who received emergency AD ALLOWED FOR THIS FLIGHT;
2006-18-51, which contained the (ii) FLIGHT INTO KNOWN OR FORECAST
requirements of this amendment and MODERATE OR SEVERE TURBULENCE IS
became effective immediately upon PROHIBITED; and
receipt. (iii) INDICATED AIRSPEED IS LIMITED
TO 175 KNOTS MAXIMUM.
(3) Repair any cracks or other Before further flight after the Contact RAC at Post Office Box 85,
damage such as loose or missing inspection required by paragraph Wichita, Kansas 67201-0085; phone:
fasteners found during the (e)(1) of this AD. 316-676-8366; fax: (316) 676-8745;
inspection required in paragraph e-mail: tom--
(e)(1) of this AD. Do this by peay@rac.ray.com.
obtaining and incorporating an FAA-
approved repair scheme from RAC.
(4) Report the inspection results to Within 72 hours after completing the Send your report to Steven E.
the FAA and RAC. For the reporting inspection required in paragraph Potter, FAA, 1801 Airport Road,
requirement in this AD, under the (e)(1) of this AD. Wichita, Kansas 67209; fax: (316)
provisions of the Paperwork 946-4107; e-mail:
Reduction Act, the Office of steven.potter@faa.gov; and Tom
Management and Budget (OMB) has Peay, Raytheon Aircraft Company,
approved the information collection Post Office Box 85, Wichita, Kansas
requirements and has assigned OMB 67201-0085; fax: (316) 676-8745; e-
Control Number 2120-0056. mail: tom_
peay@rac.ray.com.
Include in your report the
following information:
(i) Aircraft model and serial
number;
(ii) Number of cycles;
(iii) Aircraft hours TIS;
(iv) Left and right wing lower spar
cap hours TIS;
(v) Hours TIS on the spar cap since
last inspection;
(vi) Answer yes or no whether
cracking, missing fasteners, or
other damage was found; and
(vii) If cracking was found,
identify size and location of
cracks.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office, FAA,
ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas
67209; telephone: (316) 946-4124; fax: (316) 946-4107, has the
authority to approve AMOCs for this AD, if requested using the
procedures in 14 CFR 39.
APPENDIX TO AD 2006-18-51
Inspection Instructions--Raytheon Aircraft Company 1900 Series Wing
Rear Spar
Step 1. Lower the wing flaps to provide visual access to the
wing rear spar cove area. Although the pictures show the flaps
removed, this AD does not require flap removal to do the inspection.
Step 2. Using a strong, high-intensity light visually inspect
the area of the wing rear spar identified in Figure 1. There is
ample visually visual access from above the upper surface of the
flap. Look for cracks (like those shown in Figures 2 and 3) and
loose or missing fasteners.
Step 3. Clean the wing rear spar area 10 inches inboard and
outboard of the buttock line (BL) 114 area.
Step 4. Repeat the Step 2 inspection.
BILLING CODE 4910-13-U
[[Page 52986]]
[GRAPHIC] [TIFF OMITTED] TR08SE06.002
[[Page 52987]]
[GRAPHIC] [TIFF OMITTED] TR08SE06.003
[[Page 52988]]
[GRAPHIC] [TIFF OMITTED] TR08SE06.004
Issued in Kansas City, Missouri, on September 1, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-7511 Filed 9-7-06; 8:45 am]
BILLING CODE 4910-13-C
