[Federal Register: September 8, 2006 (Volume 71, Number 174)]
[Rules and Regulations]
[Page 52983-52988]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08se06-4]
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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.
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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 http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://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 http://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 http://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 http://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.
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(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.
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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]]
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Actions Compliance Procedures
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(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[fxsp0]@[fxsp0]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[fxsp0]@[fxsp0]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.
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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
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[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