Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 69739 

rounded to whole dollars for ease of 

compliance. 

The fee trigger being adjusted in this 

Federal Register notice pursuant to 

TILA section 103(bb) is used in 

determining whether a loan is covered 

by § 1026.32. Such loans have generally 

been known as ‘‘HOEPA loans.’’ In July 

2008, the Board revised Regulation Z to 

adopt additional protections for 

‘‘higher-priced mortgage loans,’’ using 

its authority under TILA section 

129(l)(2), since redesignated as section 

129(p)(2). Those revisions define a class 

of dwelling-secured transactions, 

described in § 1026.35, using a 

threshold based on average market rates. 

The adjustment published today does 

not affect the triggers adopted in July 

2008 by the Board for higher-priced 

mortgage loans. 

On July 9, 2012, the Bureau issued a 

proposed rule pursuant to, inter alia, 

section 1431 of the Dodd-Frank Act, 

which revises the statutory fee trigger 

for HOEPA loans. The Bureau is 

mindful of the need to coordinate 

implementation of this final rule with 

the effective date of the final rule 

adopting revisions to the HOEPA fee 

trigger pursuant to the July 9, 2012 

proposal. Accordingly, the adjustment 

to the fee trigger that is being published 

today will become effective on January 

1, 2013 and will apply for one year, or 

until final rules the Bureau proposed on 

July 9, 2012 to implement section 1431 

of the Dodd-Frank Act become effective, 

whichever is earlier. 

II. Adjustment and Commentary 

Revision 

Effective January 1, 2013, for purposes 

of determining whether a home 

mortgage transaction is covered by 

§ 1026.32 (based on the total points and 

fees payable by the consumer at or 

before loan closing), a loan is covered if 

the points and fees exceed the greater of 

$625 or 8 percent of the total loan 

amount. Comment 32(a)(1)(ii)–2, which 

lists the adjustments for each year, is 

amended to reflect the new dollar 

threshold amount for 2013. 

Under the Administrative Procedure 

Act, notice and opportunity for public 

comment are not required if the Bureau 

finds that notice and public comment 

are impracticable, unnecessary, or 

contrary to the public interest. 5 U.S.C. 

553(b)(B). Because the timing and 

method of the adjustment are set by 

statute and are technical and nondiscretionary, the Bureau finds that 

notice and public comment on the 

change are unnecessary. 5 U.S.C. 

553(b)(B). 

Because no notice of proposed 

rulemaking is required, the Regulatory 

Flexibility Act does not apply. 5 U.S.C. 

601(2). In any event, the Bureau certifies 

that this amendment to Regulation Z 

will not have a significant economic 

impact on a substantial number of small 

entities. The only change is to increase 

the threshold for transactions requiring 

HOEPA disclosures and protections to 

reflect the annual percentage increase in 

the CPI–U. This change is required by 

statute. Furthermore, the Bureau 

believes that the number of small 

entities that will be required to comply 

with Regulation Z’s HOEPA protections 

solely due to this adjustment because 

they offer ‘‘HOEPA’’ loans is not 

substantial. In addition, for entities that 

already offer ‘‘HOEPA’’ loans in which 

the total points and fees payable by the 

consumer at or before loan 

consummation exceed the greater of 

$400 or 8 percent of the loan amount, 

whichever is less, the Bureau believes 

the economic impact to comply with 

Regulation Z for additional ‘‘HOEPA’’ 

loans in which the total points and fees 

payable by the consumer at or before 

loan consummation exceed the greater 

of $625 or 8 percent of the loan amount, 

whichever is less, will not be 

significant. 

List of Subjects in 12 CFR Part 1026 

Advertising, Consumer protection, 

Credit, Credit unions, Mortgages, 

National banks, Reporting and 

recordkeeping requirements, Savings 

association, Truth in lending. 

Authority and Issuance 

For the reasons set forth in the 

preamble, the Bureau amends 

Regulation Z, 12 CFR part 1026, as set 

forth below: 

PART 1026—TRUTH IN LENDING 

(REGULATION Z) 

■ 1. The authority citation for part 1026 

is revised to read as follows: 

Authority: 12 U.S.C. 2601; 2603–2605, 

2607, 2609, 2617, 5511, 5512, 5532, 5581; 15 

U.S.C. 1601 et seq. 

■ 2. In Supplement I to part 1026, under 

Section 1026.32—Requirements for 

Certain Closed-End Home Mortgages, 

32(a) Coverage, paragraph 32(a)(1)(ii), 

paragraph 2 is amended by adding new 

paragraph 2.xviii to read as follows: 

SUPPLEMENT I TO PART 1026— 

OFFICIAL INTERPRETATIONS 

* * * * * 

Section 1026.32—Requirements for Certain 

Closed-End Home Mortgages 

32(a) Coverage. 

* * * * * 

Paragraph 32(a)(1)(ii). 

* * * * * 

2. Annual adjustment of $400 amount. 

* * * 

xviii. For 2013, $625, reflecting a 2.3 

percent increase in the CPI–U from June 2011 

to June 2012, rounded to the nearest whole 

dollar. 

* * * * * 

Dated: November 6, 2012. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2012–27997 Filed 11–20–12; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0498; Directorate 

Identifier 2011–NM–212–AD; Amendment 

39–17238; AD 2012–22–02] 

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 747–400, 

–400D, and –400F series airplanes. This 

AD was prompted by reports of crown 

frame web cracking at left buttock line 

(LBL) 15.0, station (STA) 320. This AD 

requires measuring the web at STA 320 

and, depending on findings, various 

inspections for cracks and missing 

fasteners, web and fastener replacement, 

and related investigative and corrective 

actions if necessary. We are issuing this 

AD to prevent complete fracture of the 

crown frame assembly, and consequent 

damage to the skin and in-flight 

decompression 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 


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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: 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. 

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 June 12, 2012 (77 FR 34881). 

That NPRM proposed to require 

measuring the web at STA 320 and, 

depending on findings, various 

inspections for cracks and missing 

fasteners, web and fastener replacement, 

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 (77 FR 34881, 

June 12, 2012), and the FAA’s response 

to each comment. 

Support for the NPRM (77 FR 34881, 

June 12, 2012) 

Mr. Caleb Berken stated that the fact 

that cracks have been seen in five of 

these airplanes is a little unnerving, but 

when it is considered that there are only 

29 airplanes of this particular series 

(Model 747–400, –400D, and –400F 

series airplanes) currently in operation 

within the United States, these statistics 

become quite alarming. The commenter 

stated that he would like to put forth his 

full support for this proposed rule (77 

FR 34881, June 12, 2012) to increase 

inspection and replacement of 

compromised parts that have developed 

within the crown frame web. 

Request To Provide Credit for Prior 

Actions 

Boeing requested that we allow credit 

for work done prior to the effective date 

of the NPRM (77 FR 34881, June 12, 

2012) using Boeing Service Bulletin 

747–53A2784, dated August 27, 2009. 

Boeing stated that Boeing Service 

Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011 (which is the 

service information referenced in the 

NPRM (77 FR 34881, June 12, 2012)), 

states that ‘‘[n]o more work is necessary 

on airplanes changed in accordance 

with the original issue of this service 

bulletin.’’ Boeing stated that the 

inspections and corrective actions 

described in Boeing Service Bulletin 

747–53A2784, dated August 27, 2009; 

and Revision 1, dated September 14, 

2011; are structurally equivalent. 

We agree to add credit for prior 

actions because no more work is 

necessary on airplanes changed in 

accordance with Boeing Service Bulletin 

747–53A2784, dated August 27, 2009. 

We have added new paragraph (l) to this 

AD to provide credit for 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. We have reidentified subsequent paragraphs 

accordingly. 

Request To Allow Deviation Authority 

Boeing requested that paragraph (1)(3) 

of the NPRM (77 FR 34881, June 12, 

2012) be revised to allow the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) to 

approve alternative methods of 

compliance (AMOCs) for both repairs 

and deviations to the modification that 

are described in either Boeing Service 

Bulletin 747–53A2784, dated August 27, 

2009; or Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 

14, 2011. Boeing requested that we 

clarify that an AMOC can be approved 

for both repairs and deviations to the 

modification, and that the modification 

described in Boeing Service Bulletin 

747–53A2784, dated August 27, 2009, 

satisfies the requirements of the 

modification described in Boeing 

Service Bulletin 747–53A2784 Revision 

1, dated September 14, 2011. 

We partially agree. The Boeing ODA 

is not currently authorized to provide 

AMOC approval of deviations that occur 

when doing the modification. However, 

once the AD is issued, we might 

delegate approval authority to certain 

authorized representatives of the Boeing 

ODA to approve AMOCs for deviations 

during this modification. We have not 

changed the AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

34881, June 12, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 34881, 

June 12, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 29 

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 

Measurement .............. 1 work-hour × $85 per hour = $85 ................. $0 ..................... $85 ............................. $2,465. 

Inspection and web replacement.208 work-hours × $85 per hour = $17,680 .... Up to $21,887 .. Up to $39,567 ............ Up to $1,147,443. 

Post-replacement inspection.135 work-hours × $85 per hour = $11,475 

per inspection cycle.

$0 ..................... $11,475 per inspection cycle.$332,775 per inspection 

cycle. 


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Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 69741 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition crack 

repairs specified in 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 

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): 

2012–22–02 The Boeing Company: 

Amendment 39–17238; Docket No. 

FAA–2012–0498; Directorate Identifier 

2011–NM–212–AD. 

(a) Effective Date 

This AD is effective December 26, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400, –400D, and –400F series 

airplanes, certificated in any category, as 

specified in Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of crown 

frame web cracking at left buttock line (LBL) 

15.0, station (STA) 320. We are issuing this 

AD to prevent complete fracture of the crown 

frame assembly, and consequent damage to 

the skin and in-flight decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Crown Frame Web Measurement 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, except 

as specified in paragraph (k)(1) of this AD, 

measure the thickness of the crown frame 

web at STA 320, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011. For airplanes with 

a 0.136- to 0.145-inch-thick web, no further 

action is required by this AD. 

(h) Detailed Inspection and Web 

Replacement With No Web Repair Doubler 

For airplanes on which the web measures 

0.078- to 0.083-inch-thick during the 

measurement required by paragraph (g) of 

this AD, and on which a repair doubler is not 

installed: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(1) of this AD, do 

a detailed inspection for cracks and a general 

visual inspection for missing fasteners of the 

crown frame web at STA 320; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(2) of this AD. Do 

the applicable related investigative and 

corrective actions at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, except 

as specified in paragraph (k)(1) of this AD. 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, 

provides options for accomplishing the 

actions that are required for airplanes on 

which no cracking is found in the crown 

frame web. 

(i) Detailed Inspection and Web 

Replacement With Web Repair Doubler 

For airplanes on which the web measures 

0.078- to 0.083-inch-thick during the 

measurement required by paragraph (g) of 

this AD, and on which a repair doubler is 

installed: At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, except 

as specified in paragraph (k)(1) of this AD, do 

the actions specified in paragraphs (i)(1) and 

(i)(2) of this AD, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(2) of this AD. Do 

all applicable corrective actions before 

further flight. 

(1) Replace the web with a new web and 

do all applicable related investigative 

actions. 

(2) Do a detailed inspection for cracks in 

the upper or lower chord of the crown frame 

web at STA 320. 

(j) Post-Replacement Repetitive Inspections 

of Replaced Web 

Following any web replacement required 

by this AD, at the times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011: Do a detailed 

inspection for cracks of the web, upper 

chord, lower chord, and lower chord splice, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011, except as specified in paragraph (k)(2) 

of this AD. Do all applicable corrective 

actions before further flight. If no crack is 

found, repeat the inspection thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2784, Revision 1, dated September 

14, 2011. Accomplishment of the inspections 

required by AD 2009–19–05, Amendment 

39–16022 (74 FR 48138, September 22, 2009), 

terminates the requirements of this 

paragraph. 

(k) Exceptions to the Service Information 

(1) Where Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 


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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 


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