Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes, 70297-70300 [E6-20326]
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Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
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 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13183 (68 FR
33621, June 5, 2003) and by adding a
new airworthiness directive,
Amendment 39–14841, to read as
follows:
I
2006–25–01 International Aero Engines
AG: Amendment 39–14841; Docket No.
FAA–2006–26013; Directorate Identifier
2003–NE–21–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 8, 2007.
Affected ADs
(b) This AD supersedes AD 2003–11–23,
Amendment 39–13183.
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Applicability
(c) This AD applies to International Aero
Engines AG (IAE) V2522–A5, V2524–A5,
V2527–A5, V2527E–A5, V2527M–A5,
V2530–A5, and V2533–A5 turbofan engines
with engine serial numbers V10601 through
V11335 inclusive and bearings part number
(P/N) 2A1165 installed. These engines are
installed on, but not limited to, Airbus
Industrie A319, A320, and A321 series
airplanes.
Unsafe Condition
(d) This AD results from IAE developing a
terminating action to the repetitive
inspections of the chip detectors, and from
expanding the applicability to include
additional serial-numbered engines with
certain No. 3 bearings installed. We are
issuing this AD to prevent failure of the No.
3 bearing, which could result in an IFSD and
smoke in the cockpit and cabin. The smoke
is a result of oil escaping from the bearing
compartment due to a fracture of the No. 3
bearing race.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
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Inspection of the Master Magnetic Chip
Detector (MCD) or the No. 1, 2, 3 Bearing
Chamber MCD
(f) For engines listed in Table 1 of
Appendix 1 of IAE Service Bulletin (SB) No.
V2500–ENG–72–0452, Revision 4, dated
September 30, 2005, and that have a No. 3
bearing, P/N 2A1165, installed at new
production build, do the following:
(1) Within 125 hours time-in-service (TIS)
after the effective date of this AD, inspect the
master MCD or the No. 1, 2, 3 bearing
chamber MCD.
(2) Thereafter, within 125 hours timesince-last inspection, inspect the master MCD
or the No. 1, 2, 3 bearing chamber MCD.
(3) If you find bearing material on the
master MCD or No. 1, 2, 3 bearing chamber
MCD, remove the engine from service before
further flight.
Inspection Recommendation
(g) We recommend the inspection of the
master MCD or the No. 1, 2, 3 bearing
chamber MCD, using paragraphs (f) through
(f)(3) of this AD, on all engines installed on
the same airplane, not be done by the same
individual before the same flight. This is to
minimize the chances of maintenance error
on multiple engine airplanes.
Removal of No. 3 Bearing
(h) At the next shop visit, for engines listed
in Table 1 of Appendix 1 of IAE SB No.
V2500–ENG–72–0452, Revision 4, dated
September 30, 2005, that have a serial
number (SN) from V10601 through V11335
inclusive, and that have a No. 3 bearing,
P/N 2A1165 installed at new production,
remove the No. 3 bearing.
(i) After the effective date of this AD, do
not install any No. 3 bearing, P/N 2A1165,
removed in paragraph (h) of this AD, into any
engine.
Removal of High Pressure Compressor (HPC)
Stubshaft
(j) At the next shop visit, for engines listed
in Table 1 of Appendix 1 of IAE SB No.
V2500–ENG–72–0452, Revision 4, dated
September 30, 2005, that have a SN from
V10601 through V11335 inclusive, remove
the HPC stubshaft that has a low-energy
plasma coating.
Terminating Action
(k) Performing the requirements specified
in paragraph (h) and (j) of this AD is
terminating action to the repetitive MCD
inspections specified in paragraphs (f)
through (f)(3) of this AD.
Alternative Methods of Compliance
(l) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(m) For identifying engines within the
engine SN range of V10601 to V11335
inclusive, known to have had P/N 2A1165
installed, you must use Table 1 of Appendix
1 of International Aero Engines Service
Bulletin No. V2500–ENG–72–0452, Revision
4, dated September 30, 2005. The Director of
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70297
the Federal Register approved the
incorporation by reference of Table 1 of
Appendix 1 of International Aero Engines
Service Bulletin No. V2500–ENG–72–0452,
Revision 4, dated September 30, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact International Aero Engines
AG, 400 Main Street, East Hartford, CT
06108; telephone: (860) 565–5515; fax: (860)
565–5510, for a copy of this service
information. You may review copies at the
FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive
Park, Burlington, MA; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Related Information
(n) The following SBs contain additional
information and procedures:
(1) You can find information on inspecting
the master MCD and the No. 1, 2, 3 bearing
chamber MCD in section 79–00–00–601 of
the Aircraft Maintenance Manual.
(2) Additional information on inspection
procedures is included in IAE SB No. V2500–
ENG–72–0452, Revision 4, dated September
30, 2005.
(3) You can find information on replacing
the No. 3 bearing in IAE SB No. V2500–ENG–
72–0459, Revision 3, dated April 12, 2003.
(4) You can find information on replacing
HPC stubshafts that have a low-energy
plasma coating, (all engines) in IAE SB No.
V2500–ENG–72–0460, Revision 2, dated
March 4, 2006.
(o) Airworthiness directive 2003–10–14
and AD 2003–13–02, which revise the
Limitation section of the airplane flight
manual to incorporate new procedures to
follow in the event of smoke in the cockpit
and cabin, are related to the subject of this
AD.
Issued in Burlington, Massachusetts, on
November 27, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–20323 Filed 12–1–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26258; Directorate
Identifier 2006–CE–67–AD; Amendment 39–
14840; AD 2006–24–11]
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:
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Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Raytheon Aircraft Company (RAC)
Models 1900, 1900C, and 1900D
airplanes. This AD requires you to
repetitively inspect the forward,
vertical, and aft flanges of both the left
and right wing rear spar lower caps for
cracks, repair any cracks found, and
report the inspection results to RAC.
This AD results from additional fatigue
cracks found in this area since
inspections were performed to comply
with Emergency AD 2006–18–51, which
required immediate visual inspections
of this area. We are issuing this AD for
the purpose of performing a more
rigorous inspection requiring cleaning
and paint stripping of this section of the
wing rear spar to detect and correct
cracking in the wing spar lower caps of
the affected airplanes before the cracks
lead to failure. These wing rear spar
cracks may result in wing failure which
could result in the wing separating from
the airplane with consequent loss of
control.
This AD becomes effective on
December 11, 2006.
As of December 11, 2006, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
We must receive any comments on
this AD by February 2, 2007.
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 get the service information
identified in this AD, contact Raytheon
Aircraft Company (RAC), Post Office
Box 85, Wichita, Kansas 67201–0085,
Phone 1–800–429–5372 or 1–316–676–
2000, Fax: 1–316–676–8745.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2006–26258;
Directorate Identifier 2006–CE–67–AD.
FOR FURTHER INFORMATION CONTACT:
Steven E. Potter, FAA, 1801 Airport
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DATES:
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Road, Wichita, Kansas 67209;
telephone: (316) 946–4124; fax: (316)
946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
Due to significant cracks found in the
wing rear spar of RAC Model 1900D
airplanes, we issued Emergency AD
2006–18–51 on August 31, 2006. AD
2006–18–51 required an immediate
visual inspection of both the left and
right wing rear spars near the outboard
edge of the engine nacelle. This AD was
then published in the Federal Register
as Amendment 39–14757 (71 FR 52983,
September 8, 2006).
Additional fatigue cracks in the
affected area of the wing rear spar have
been found since the AD 2006–18–51
inspections were performed. One of the
airplanes had accumulated 168 hours
time-in-service (TIS) since the visual
inspections required by AD 2006–18–51
were done.
The FAA has determined a more
rigorous and detailed inspection is
necessary to find such fatigue cracks.
Cracking in the wing rear spar lower
caps and adjacent structure, 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.
Relevant Service Information
We reviewed Raytheon Aircraft
Company Service Bulletin No. 57–3815,
Issued: October, 2006. The service
information describes procedures for the
left and right rear wing spar lower cap
inspection.
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
have evaluated all known and available
information and determined the unsafe
condition described previously is likely
to exist or develop on other products of
the same type design. This AD requires
a rigorous and detailed inspection of the
wing rear spar lower caps to find the
fatigue cracks. The preparation and
procedural requirements for these
inspections are included in RAC
Mandatory Service Bulletin 57–3815.
RAC is developing a modification
that, if approved by the FAA, would
terminate the repetitive inspection
requirement of this AD. The FAA may
take future rulemaking action on this
subject.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
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opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and 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–
2006–26258; Directorate Identifier
2006–CE–67–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.
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Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations
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.
70299
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
not supersede or revise that AD. Both ADs
are necessary to address the unsafe
condition.
Adoption of the Amendment
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
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
Applicability
Models
Serial numbers
(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 ..................
Authority: 49 U.S.C. 106(g), 40113, 44701.
Examining the AD Docket
§ 39.13
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.
I
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2006–24–11 Raytheon Aircraft Company
(RAC): Amendment 39–14840; Docket
No. FAA–2006–26258; Directorate
Identifier 2006–CE–67–AD.
Effective Date
(a) This AD becomes effective on December
11, 2006.
Affected ADs
(b) AD 2006–18–51, Amendment 39–14757
(71 FR 52983, September 8, 2006), relates to
the subject of this AD. However, this AD does
Unsafe Condition
(d) This AD is the result of additional
fatigue cracks found in the wing rear spar
lower caps on a Raytheon Model 1900
airplane shortly after complying with AD
2006–18–51. We are issuing this AD to
require a more rigorous and detailed
inspection to find the fatigue cracks which
are the unsafe condition. Failure to detect
cracking in the wing rear spar lower caps of
the affected airplanes could result in a wing
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, unless already done:
Compliance
Procedures
(1) Repetitively inspect both the left and right
wing rear spar lower caps for cracks and
other damage such as loose or missing fasteners.
Initially inspect within 100 hours time-in-service (TIS) or 30 days after December 11,
2006 (the effective date of this AD), whichever occurs first. Repetitively inspect thereafter at intervals not to exceed 200 hours
TIS.
Follow the procedures in Raytheon Mandatory
Service Bulletin 57–3815, dated Issued: October, 2006.
(2) If cracks are found repair all cracks by obtaining and incorporating an FAA-approved
repair scheme from RAC.
Before further flight after any inspection required by paragraph (e)(1) of this AD where
cracks are found.
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.
(3) Report the inspection results to Raytheon
Aircraft Company using the instructions and
forms in the service bulletin. Complete all
sections of the required forms. Reporting requirements have been approved by the Office of Management and Budget (OMB) and
assigned OMB control number 2120–0056.
Report the initial inspection within 10 days
after the inspection or 10 days after the effective date of this AD, whichever occurs
later. Report the repetitive inspections within
30 days after the inspection.
Follow the procedures in Raytheon Mandatory
Service Bulletin 57–3815, dated Issued: October, 2006.
Alternative Methods of Compliance
(AMOCs)
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Actions
2006, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Raytheon Aircraft Company
(RAC), Post Office Box 85, Wichita, Kansas
67201–0085, Phone 1–800–429–5372 or 1–
316–676–2000, Fax: 1–316–676–8745.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(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.
Material Incorporated by Reference
(g) You must use Raytheon Mandatory
Service Bulletin 57–3815, Issued: October,
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Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations
Issued in Kansas City, Missouri, on
November 24, 2006.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–20326 Filed 12–1–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25810; Directorate
Identifier 2006–CE–49–AD; Amendment 39–
14838; AD 2006–24–09]
RIN 2120–AA64
Airworthiness Directives; PZL-Bielsko
Model SZD–50–3 ‘‘Puchacz’’ Gliders
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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12:11 Dec 01, 2006
Jkt 211001
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 AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
Discussion
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as a discrepancy between the
design documentation and the
Technical Service Manual. In 1981, a
castellated nut with cotter pin was
introduced to secure the rudder,
replacing the self-locking nut through
PZL-Bielsko Bulletin No. BE–06/50–3/
81. This change has not been introduced
to the Technical Service Manual and
use of a self-locking nut, in accordance
with the Manual, is still possible. We
are issuing this AD to require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
January 8, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 8, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Gregory Davison, Glider Program
Manager, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816)
329–4130; fax: (816) 329–4090.
SUMMARY:
SUPPLEMENTARY INFORMATION:
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 27, 2006 (71 FR
56416). That NPRM proposed to correct
an unsafe condition for the specific
products. The MCAI states that a
discrepancy between the design
documentation and the Technical
Service Manual has been identified. In
1981, a castellated nut with cotter pin
was introduced to secure the rudder,
replacing the self-locking nut through
PZL-Bielsko Bulletin No BE–06/50–3/
81. This change has not been introduced
to the Technical Service Manual and
use of a self-locking nut, in accordance
with the Manual, is still possible. This
was probably the reason of rudder
disconnection during flight which
occurred recently. If not corrected, loss
of the nut could result and allow the
rudder to slip out of its hinges, separate
from the glider, and lead to loss of
control. This AD requires you to inspect
and, if necessary, replace the Rudder
Attachment parts in accordance with
the instruction contained in the Allstar
PZL Glider Sp. z o.o. Mandatory
Bulletin No. BE–058/SZD–50–3/2006
‘‘PUCHACZ’’, dated August 10, 2006.
Concurrently, changes in the Technical
Service Manual must be introduced in
accordance with the referenced bulletin.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
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Jack Buster with the Modification and
Replacement Parts Association
(MARPA) provides comments to the
MCAI AD process pertaining to how the
FAA addresses publishing manufacturer
service information as part of a
proposed AD action. Mr. Buster states
that the rule, as proposed, attempts to
require compliance with a public law by
reference to a private writing (as
referenced in paragraph (e) of the
proposed AD). Mr. Buster would like
the FAA to incorporate by reference
(IBR) the Allstar PZL Glider Sp. z o.o.
Mandatory Bulletin.
We agree with Mr. Buster. However,
we do not IBR any document in a
proposed AD action, instead we IBR the
document in the final rule. Since we are
issuing the proposal as a final rule AD
action, Allstar PZL Glider Sp. z o.o.
Mandatory Bulletin No. BE–058/SZD–
50–3/2006 ‘‘PUCHACZ’’, dated August
10, 2006, is incorporated by reference.
Mr. Buster requests that IBR
documents be made available to the
public by publication in the Federal
Register or in the Docket Management
System (DMS).
We are currently reviewing issues
surrounding the posting of service
bulletins in the Department of
Transportation’s DMS as part of the AD
docket. Once we have thoroughly
examined all aspects of this issue and
have made a final determination, we
will consider whether our current
practice needs to be revised.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable in a U.S.
court of law. In making these changes,
we do not intend to differ substantively
from the information provided in the
MCAI and related service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are described in a
separate paragraph of the AD. These
requirements, if any, take precedence
over the actions copied from the MCAI.
E:\FR\FM\04DER1.SGM
04DER1
]]>Agencies
[Federal Register Volume 71, Number 232 (Monday, December 4, 2006)]
[Rules and Regulations]
[Pages 70297-70300]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20326]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26258; Directorate Identifier 2006-CE-67-AD;
Amendment 39-14840; AD 2006-24-11]
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.
-----------------------------------------------------------------------
[[Page 70298]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D
airplanes. This AD requires you to repetitively inspect the forward,
vertical, and aft flanges of both the left and right wing rear spar
lower caps for cracks, repair any cracks found, and report the
inspection results to RAC. This AD results from additional fatigue
cracks found in this area since inspections were performed to comply
with Emergency AD 2006-18-51, which required immediate visual
inspections of this area. We are issuing this AD for the purpose of
performing a more rigorous inspection requiring cleaning and paint
stripping of this section of the wing rear spar to detect and correct
cracking in the wing spar lower caps of the affected airplanes before
the cracks lead to failure. These wing rear spar cracks may result in
wing failure which could result in the wing separating from the
airplane with consequent loss of control.
DATES: This AD becomes effective on December 11, 2006.
As of December 11, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
We must receive any comments on this AD by February 2, 2007.
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 get the service information identified in this AD, contact
Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas
67201-0085, Phone 1-800-429-5372 or 1-316-676-2000, Fax: 1-316-676-
8745.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2006-26258; Directorate Identifier 2006-CE-67-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
Due to significant cracks found in the wing rear spar of RAC Model
1900D airplanes, we issued Emergency AD 2006-18-51 on August 31, 2006.
AD 2006-18-51 required an immediate visual inspection of both the left
and right wing rear spars near the outboard edge of the engine nacelle.
This AD was then published in the Federal Register as Amendment 39-
14757 (71 FR 52983, September 8, 2006).
Additional fatigue cracks in the affected area of the wing rear
spar have been found since the AD 2006-18-51 inspections were
performed. One of the airplanes had accumulated 168 hours time-in-
service (TIS) since the visual inspections required by AD 2006-18-51
were done.
The FAA has determined a more rigorous and detailed inspection is
necessary to find such fatigue cracks.
Cracking in the wing rear spar lower caps and adjacent structure,
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.
Relevant Service Information
We reviewed Raytheon Aircraft Company Service Bulletin No. 57-3815,
Issued: October, 2006. The service information describes procedures for
the left and right rear wing spar lower cap inspection.
FAA's Determination and Requirements of This AD
We are issuing this AD because we have evaluated all known and
available information and determined the unsafe condition described
previously is likely to exist or develop on other products of the same
type design. This AD requires a rigorous and detailed inspection of the
wing rear spar lower caps to find the fatigue cracks. The preparation
and procedural requirements for these inspections are included in RAC
Mandatory Service Bulletin 57-3815.
RAC is developing a modification that, if approved by the FAA,
would terminate the repetitive inspection requirement of this AD. The
FAA may take future rulemaking action on this subject.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and 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-
26258; Directorate Identifier 2006-CE-67-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.
[[Page 70299]]
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, Incorporation by
reference, 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):
2006-24-11 Raytheon Aircraft Company (RAC): Amendment 39-14840;
Docket No. FAA-2006-26258; Directorate Identifier 2006-CE-67-AD.
Effective Date
(a) This AD becomes effective on December 11, 2006.
Affected ADs
(b) AD 2006-18-51, Amendment 39-14757 (71 FR 52983, September 8,
2006), relates to the subject of this AD. However, this AD does not
supersede or revise that AD. Both ADs are necessary to address the
unsafe condition.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Models Serial numbers
------------------------------------------------------------------------
(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 additional fatigue cracks found in
the wing rear spar lower caps on a Raytheon Model 1900 airplane
shortly after complying with AD 2006-18-51. We are issuing this AD
to require a more rigorous and detailed inspection to find the
fatigue cracks which are the unsafe condition. Failure to detect
cracking in the wing rear spar lower caps of the affected airplanes
could result in a wing 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, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Repetitively inspect both Initially inspect Follow the
the left and right wing rear within 100 hours procedures in
spar lower caps for cracks and time-in-service Raytheon
other damage such as loose or (TIS) or 30 days Mandatory Service
missing fasteners. after December Bulletin 57-3815,
11, 2006 (the dated Issued:
effective date of October, 2006.
this AD),
whichever occurs
first.
Repetitively
inspect
thereafter at
intervals not to
exceed 200 hours
TIS.
------------------------------------------------------------------------
(2) If cracks are found repair Before further Contact RAC at
all cracks by obtaining and flight after any Post Office Box
incorporating an FAA-approved inspection 85, Wichita,
repair scheme from RAC. required by Kansas 67201-
paragraph (e)(1) 0085; phone: 316-
of this AD where 676-8366; fax:
cracks are found. (316) 676-8745; e-
mail: tom_
peay@rac.ray.com.
------------------------------------------------------------------------
(3) Report the inspection Report the initial Follow the
results to Raytheon Aircraft inspection within procedures in
Company using the instructions 10 days after the Raytheon
and forms in the service inspection or 10 Mandatory Service
bulletin. Complete all sections days after the Bulletin 57-3815,
of the required forms. effective date of dated Issued:
Reporting requirements have this AD, October, 2006.
been approved by the Office of whichever occurs
Management and Budget (OMB) and later. Report the
assigned OMB control number repetitive
2120-0056. inspections
within 30 days
after the
inspection.
------------------------------------------------------------------------
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.
Material Incorporated by Reference
(g) You must use Raytheon Mandatory Service Bulletin 57-3815,
Issued: October, 2006, to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas
67201-0085, Phone 1-800-429-5372 or 1-316-676-2000, Fax: 1-316-676-
8745.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.
[[Page 70300]]
Issued in Kansas City, Missouri, on November 24, 2006.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-20326 Filed 12-1-06; 8:45 am]
BILLING CODE 4910-13-P
