Document ID: FAA-2010-0042-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA00244WI-D, ST00146WI-D, or SA984GL-D
Posted Date: 2010-01-19T05:00Z

[Federal Register Volume 75, Number 11 (Tuesday, January 19, 2010)]
[Proposed Rules]
[Pages 2829-2831]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-698]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0042; Directorate Identifier 2009-NM-010-AD]
RIN 2120-AA64

Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 
340A (SAAB/SF340A) and SAAB 340B Airplanes Modified in Accordance With 
Supplemental Type Certificate (STC) SA00244WI-D, ST00146WI-D, or 
SA984GL-D

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and 
SAAB 340B airplanes. This proposed AD would require inspecting the 
fuselage surface for corrosion and cracking behind the external adapter 
plate of the antennae installation, and repair if necessary. This 
proposed AD results from a report of a crack found behind the external 
adapter plate of the antennae during inspection. Similar cracking was 
found on two additional airplanes, and extensive corrosion was found on 
one airplane. We are proposing this AD to detect and correct corrosion 
and cracking behind the external adapter plate of the antennae of 
certain safe-life structure, which could result in reduced structural 
integrity and consequent rapid depressurization of the airplane.

DATES: We must receive comments on this proposed AD by March 5, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

[[Page 2830]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.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 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: William Griffith, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
67209; telephone (316) 946-4116; fax (316) 946-4107.

SUPPLEMENTARY INFORMATION:

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-2010-0042; 
Directorate Identifier 2009-NM-010-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 closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We received a report of a crack found behind the external adapter 
plate of the antennae during inspection of a Model SAAB 340A airplane, 
serial number 142. Similar cracking was found on two additional 
airplanes, and extensive corrosion was found on one airplane. These 
airplanes had Supplemental Type Certificate (STC) work done by a common 
installer. Investigation revealed that insufficient corrosion 
protection was applied during installation. No known data show that 
other airplanes with work done elsewhere in accordance with STC 
SA00244WI-D, ST00146WI-D, or SA984GL-D have had common corrosion 
issues. The STC data provided show sufficient corrosion protection is 
specified in STCs SA00244WI-D, ST00146WI-D, and SA984GL-D for other 
airplanes, and the unsafe condition is limited to airplanes on which 
the identified STC work was done. Corrosion and cracking behind the 
external adapter plate of the antennae of certain safe-life structure 
if not detected and corrected, could result in reduced structural 
integrity and consequent rapid depressurization of the airplane.
    The subject area on certain Model SAAB 340B airplanes is almost 
identical to that on the affected Model SAAB 340A airplanes. Therefore, 
those Model SAAB 340B airplanes may be subject to the unsafe condition 
revealed on the Model SAAB 340A airplanes.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in Sweden and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement.
    We are proposing this AD, which would require inspecting the 
fuselage surface for corrosion or cracking behind the external adapter 
plate of the Supplemental Type Certificate antennae installation. This 
proposed AD also would require repair of any corrosion or cracking 
found. All actions, including any repairs, are required to be done in 
accordance with a method approved by the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For airplanes on which no corrosion or 
cracking is found, the proposed AD would require ensuring that proper 
corrosion protection has been applied before reinstalling the adapter 
plate, in accordance with a method approved by the Manager, Wichita 
ACO.
    This proposed AD does not provide credit for actions that may have 
already been done to address the identified unsafe condition since no 
FAA-approved method for accomplishing the required actions exists. 
However, if any operator already has removed the adapter plate and done 
a repair, that operator may request approval of an alternative method 
of compliance (AMOC) under the provisions of paragraph (j) of this 
proposed AD.

Costs of Compliance

    This proposed AD would affect about 201 airplanes of U.S. registry. 
The proposed inspection would take about 4 work hours per airplane, at 
an average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $64,320, or 
$320 per airplane.

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. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

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:

[[Page 2831]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Saab AB, Saab Aerosystems: Docket No. FAA-2010-0042; Directorate 
Identifier 2009-NM-010-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 5, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Saab AB, Saab Aerosystems airplanes, 
certificated in any category, identified in paragraphs (c)(1) and 
(c)(2) of this AD, that have been modified in accordance with 
Supplemental Type Certificate (STC) SA00244WI-D, ST00146WI-D, or 
SA984GL-D.
    (1) Model SAAB 340A (SAAB/SF340A) airplanes, serial numbers 004 
through 159 inclusive.
    (2) Model SAAB 340B airplanes, serial numbers 160 through 459 
inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from a report of a crack found behind the 
external adapter plate of the antennae during inspection. Similar 
cracking was found on two additional airplanes, and extensive 
corrosion was found on one airplane. The Federal Aviation 
Administration is issuing this AD to detect and correct corrosion 
and cracking behind the external adapter plate of the antennae of 
certain safe-life structure, which could result in reduced 
structural integrity and consequent rapid depressurization of the 
airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified.

Inspection/Corrective Actions

    (g) Within 600 flight cycles after the effective date of this 
AD: Remove the external adapter plate of the antennae installation 
and do a general visual inspection of the fuselage surface for 
corrosion and cracking behind the external adapter plate of the 
antennae installation. If any corrosion or cracking is found, repair 
before further flight. If no corrosion or cracking is found, before 
further flight, ensure that proper corrosion protection has been 
applied before reinstalling the adapter plate. Do all the actions 
required by this paragraph in accordance with a method approved by 
the Manager, Wichita Aircraft Certification Office (ACO), FAA.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual 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.''

Reporting Requirement

    (h) At the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD: Submit a report of the positive findings of the 
inspections required by paragraph (g) of this AD. Send the report to 
the Manager, Wichita ACO. The report must contain, at a minimum, the 
inspection results, a description of any discrepancies found, the 
airplane serial number, and the number of flight cycles and flight 
hours on the airplane since installation of the STC. Under the 
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), 
the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Special Flight Permit

    (i) Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), may be issued to operate the airplane to a location 
where the requirements of this AD can be accomplished, but 
concurrence by the Manager, Wichita ACO, FAA, is required prior to 
issuance of the special flight permit.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, Wichita ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send information to ATTN: William Griffith, Aerospace 
Engineer, Airframe Branch, ACE-118W, FAA, Wichita ACO, 1801 Airport 
Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; 
telephone (316) 946-4116; fax (316) 946-4107. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
principal maintenance inspector (PMI) or principal avionics 
inspector (PAI), as appropriate, or lacking a principal inspector, 
your local Flight Standards District Office. The AMOC approval 
letter must specifically reference this AD.

Related Information

    (k) None.

    Issued in Renton, Washington, on January 7, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-698 Filed 1-15-10; 8:45 am]
BILLING CODE 4910-13-P