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

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. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

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 identified 

unsafe 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: 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

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

§ 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, Wichita 

ACO, 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. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS