### 2829 Federal Register / Vol. 75, No. 11 / Tuesday, January 19, 2010 / Proposed Rules

104–1 and 90–000200–104–2, in accordance with Part One of Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001:

(i) Before 6,000 flight hours on the backrest link since new.

(ii) Within 900 flight hours or 5 months after the effective date of this AD, whichever occurs later.

(2) If, during the inspection required by paragraph (f)(1) of this AD, cracking is found between the side of the backrest link and the lock-out pin hole but the cracking does not pass this lock-out pin hole (refer to Figure 2 of Sicma Aero Seat Service Bulletin 90–25– 013, Issue 3, dated December 19, 2001): Within 600 flight hours or 3 months after doing the inspection, whichever occurs first, replace both backrest links of the affected seat with new, improved backrest links having P/Ns 90–100200–104–1 and 90– 100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25– 013, Issue 3, dated December 19, 2001.

(3) If, during the inspection required by paragraph (f)(1) of this AD, cracking is found that passes beyond the lock-out pin hole (refer to Figure 2 of Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001): Before further flight, replace both backrest links of the affected seat with new, improved backrest links having P/Ns 90– 100200–104–1 and 90–100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001.

(4) If no cracking is found during the inspection required by paragraph (f)(1) of this AD: Do the replacement required by paragraph (f)(5) of this AD at the compliance time specified in paragraph (f)(5) of this AD.

(5) At the later of the compliance times specified in paragraphs (f)(5)(i) and (f)(5)(ii) of this AD, replace the links, P/Ns 90– 000200–104–1 and 90–000200–104–2, with new improved links, P/Ns 90–100200–104–1 and 90–100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001. Doing this replacement for an affected passenger seat assembly terminates the inspection requirements of paragraph (f)(1) of this AD for that passenger seat assembly.

(i) Before 12,000 flight hours on the backrest links, P/Ns 90–000200–104–1 and 90–000200–104–2, since new.

(ii) Within 900 flight hours or 5 months after the effective date of this AD, whichever occurs later.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: The MCAI specifies doing repetitive inspections for cracking of links having over 12,000 flight hours since new until the replacement of the link is done. This AD does not include those repetitive inspections because we have reduced the compliance time for replacing those links. This AD requires replacing the link before 12,000 flight hours since new or within 900 flight hours or 5 months of the effective date of this AD, whichever occurs latest. Other FAA AD Provisions (g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Boston Aircraft Certification Office, 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: Jeffrey Lee, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7161; fax (781) 238–7170. 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.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, 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 and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to MCAI French Airworthiness Directive 2001–613(AB), dated December 12, 2001; and Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001, including Annex 1, Issue 1, dated June 26, 2001; for related information.

Issued in Renton, Washington, on January
8, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–697 Filed 1–15–10; 8:45 am]

**BILLING CODE 4910–13–P 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).

**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.


### 2830 Federal Register / Vol. 75, No. 11 / Tuesday, January 19, 2010 / Proposed Rules

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, MidContinent 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 identifiedunsafe condition since no FAAapproved 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:


### 2831 Federal Register / Vol. 75, No. 11 / Tuesday, January 19, 2010 / Proposed Rules

**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.

**§ 39.13 [Amended]**

2. The Federal Aviation Administration (FAA) amends § 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, WichitaACO, 1801 Airport Road, Room 100, MidContinent 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**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0043; Directorate Identifier 2009–NM–128–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; McDonnell Douglas Corporation Model DC–10–10,**  **DC–10–10F, and MD–10–10F Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model DC–10–10, DC–10–10F, and MD–10–10F airplanes.This proposed AD would require a onetime high frequency eddy current inspection of fastener holes for cracks at the left and right side wing rear spar lower cap at station Xors=345, and other specified and corrective actions if necessary. This proposed AD results from a report of three instances of Model DC–10–10F airplanes having fuel leaks in the wing rear spar lower cap at station Xors=345. We are proposing this AD to prevent cracks in the spar cap, which if not corrected could lead to cracking of the lower wing skin, fuel leaks, and the inability of the structure to sustain limit load.

**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.