69742 Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 

2011, specifies a compliance time ‘‘after the 

original issue date of the service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011, specifies to contact Boeing for 

appropriate action, accomplish applicable 

actions before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) through (j) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Service Bulletin 747–53A2784, dated 

August 27, 2009. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

For more information about this AD, Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 425– 

917–6432; fax: 425–917–6590; email: Bill.

Ashforth@faa.gov. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://www.myboeingfleet.

com. 

(4) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference 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: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

19, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–27637 Filed 11–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1084; Directorate 

Identifier 2010–CE–056–AD; Amendment 

39–17257; AD 2012–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Cessna Aircraft Company (Cessna) 

Model 402C airplanes modified by 

Supplemental Type Certificate (STC) 

SA927NW and Model 414A airplanes 

modified by STC SA892NW. This AD 

was prompted by report of a Cessna 

Model 414A airplane modified by STC 

SA892NW that experienced an 

asymmetrical flap condition causing an 

uncommanded roll when the pilot set 

the flaps to the approach position. We 

are issuing this AD to prevent failure of 

the flap system, which could result in 

an asymmetrical flap condition. This 

condition could result in loss of control. 

DATES: This AD is effective December 

26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 26, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Sierra 

Industries, Ltd, 122 Howard Langford 

Drive, Uvalde, Texas 78801; telephone: 

888–835–9377; email: chip@sijet.com; 

Internet: http://www.sijet.com/r-stolhigh. You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael A. Heusser, Program Manager, 

Fort Worth Airplane Certification 

Office, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; phone: (817) 222– 

5038; fax: (817) 222–5160; email: 

michael.a.heusser@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on August 23, 2012 (77 FR 

50954). The original NPRM (75 FR 

66700, October 29, 2010) proposed to 

require a complete inspection of the flap 

system and modification of the flap 

control system. The SNPRM (77 FR 

50954, August 23, 2012) proposed to 

incorporate additional service 

information that addresses proper 

rigging procedures and corrective 

actions following additional inspection 

procedures. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(77 FR 50954, August 23, 2012) or on 

the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 69743 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

50954, August 23, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Costs of Compliance 

We estimate that this proposed AD 

affects 150 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect the flap system and modify/replace 

the flap preselect control cable.

25 work-hours × $85 per hour = $2,125 ........ $1,000 $3,125 $468,750 

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 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 FAA amends 14 CFR part 39 as 

follows: 

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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–23–01 Cessna Aircraft Company: 

Amendment 39–17257; Docket No. 

FAA–2010–1084; Directorate Identifier 

2010–CE–056–AD. 

(a) Effective Date 

This AD is effective December 26, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Cessna Aircraft 

Company (Cessna) Model 402C airplanes 

modified by Supplemental Type Certificate 

(STC) SA927NW and Model 414A airplanes 

modified by STC SA892NW, all serial 

numbers, that are certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

Cessna Model 414A airplane modified by 

STC SA892NW that experienced an 

asymmetrical flap condition causing an 

uncommanded roll when the pilot set the 

flaps to the approach position. We are issuing 

this AD to prevent failure of the flap system, 

which could result in an asymmetrical flap 

condition. This condition could result in loss 

of control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of the Flap Control System 

Within 60 days after December 26, 2012 

(the effective date of this AD), do a complete 

inspection of the flap control system 

following the Inspection Instructions section 

of Sierra Industries, Ltd. Service Bulletin 

SI09–82 Series-1, Rev. A, dated June 12, 

2012. 

(h) Modification of the Flap Control System 

(1) If any damage to the flap bellcrank or 

bellcrank mounting structure is found in the 

inspection required in paragraph (g) of this 

AD, before further flight, repair the damage 

and modify the flap control system following 

the Accomplishment Instructions of Sierra 

Industries, Ltd. Service Bulletin SI09–82 

Series-1, Rev. A, dated June 12, 2012. 

(2) If no damage to the flap bellcrank or 

bellcrank mounting structure is found in the 

inspection required in paragraph (g) of this 

AD, within 180 days after December 26, 2012 

(the effective date of this AD), modify the 

flap control system following the 

Accomplishment Instructions of Sierra 

Industries, Ltd. Service Bulletin SI09–82 

Series-1, Rev. A, dated June 12, 2012. 

(i) Instructions for Continued Airworthiness 

Within 7 months after December 26, 2012 

(the effective date of this AD), or during your 

next annual inspection, whichever occurs 

earlier, incorporate Sierra Industries, Ltd. 

Instructions for Continued Airworthiness, 

82–1, Issue 1, dated June 12, 2012, into your 

FAA-approved maintenance program. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth Airplane 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

(1) For more information about this AD, 

contact Michael A. Heusser, Program 

Manager, Fort Worth ACO, FAA, 2601 


emcdonald on DSK67QTVN1PROD with RULES
69744 Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 

Meacham Blvd., Fort Worth, Texas 76137; 

phone: (817) 222–5038; fax: (817) 222–5160; 

email: michael.a.heusser@faa.gov. 

(2) For service information identified in 

this AD, contact Sierra Industries, Ltd., 122 

Howard Langford Drive, Uvalde, Texas 

78801; telephone: 888–835–9377; email: 

chip@sijet.com; Internet: http:// 

www.sijet.com/r-stol-high. You may review 

copies of the service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use the service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Sierra Industries, Ltd. Service Bulletin 

SI09–82 Series-1, Rev. A, dated June 12, 

2012. 

(ii) Sierra Industries, Ltd. Instructions for 

Continued Airworthiness, 82–1, Issue 1, 

dated June 12, 2012. 

(3) For Sierra Industries, Ltd. service 

information identified in this AD, contact 

Sierra Industries, Ltd., 122 Howard Langford 

Drive, Uvalde, Texas 78801; telephone: 888– 

835–9377; email: chip@sijet.com; Internet: 

http://www.sijet.com/r-stol-high. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

(5) You may view this service information 

that is incorporated by reference 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: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on 

November 5, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–27456 Filed 11–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1168; Directorate 

Identifier 2010–NM–239–AD; Amendment 

39–17255; AD 2012–22–17] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200 

and –300 series airplanes. This AD was 

prompted by reports of cracks in the 

inner chords at both left-side and rightside stations 859.5, 883.5, and 903.5. 

This AD requires repetitive inspections 

of the frame inner chord transition 

radius for cracks, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent large cracks in the frames and 

adjacent structure that can adversely 

affect the structural integrity of the 

airplane. 

DATES: This AD is effective December 

26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 26, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6577; 

fax: 425–917–6590; email: 

Berhane.Alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

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 published in the Federal 

Register on November 9, 2011 (76 FR 

69685). That NPRM proposed to require 

repetitive inspections of the frame inner 

chord transition radius for cracks, and 

related investigative and corrective 

actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 69685, 

November 9, 2011) and the FAA’s 

response to each comment. 

Statement of Intent To Comply With the 

NPRM (76 FR 69685, November 9, 

2011) 

American Airlines stated that it will 

incorporate the NPRM (76 FR 69685, 

November 9, 2011) requirements into its 

maintenance program and that any 

corrective actions will be performed at 

a time that is appropriate based on the 

compliance thresholds in the NPRM. 

Request To Revise Note 1 to Paragraph 

(g) of the NPRM (76 FR 69685, 

November 9, 2011) 

Boeing requested that we revise the 

wording of Note 1 to paragraph (g) of the 

NPRM (76 FR 69685, November 9, 2011) 

to clarify that structural inspections of 

fuselage structure are mandated by AD 

2003–18–10, Amendment 39–13301 (68 

FR 53503, September 11, 2003). (AD 

2003–18–10 requires revising the 

airworthiness limitations section of the 

maintenance planning data document to 

incorporate certain inspections and 

compliance times to detect fatigue 

cracking of principal structural 

elements.) Boeing stated that an 

alteration of these structural inspections 

will be required for repair(s) done in 

accordance with Boeing Service Bulletin 

767–53A0209, Revision 1, dated July 27, 

2011. That service bulletin contains 

post-repair inspections that already 

provide alternative method of 

compliance (AMOC) coverage for the 

requirements of AD 2003–18–10. 

We disagree with the commenter’s 

request. Paragraph F., ‘‘Approval,’’ of 

Boeing Service Bulletin 767–53A0209, 

Revision 1, dated July 27, 2011, already 

contains approval of the inspections as 

an AMOC for the requirements of the 

pertinent paragraphs of AD 2003–18–10, 

Amendment 39–13301 (68 FR 53503, 

September 11, 2003). We have not 

changed the final rule in this regard. 


emcdonald on DSK67QTVN1PROD with RULES