37448 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 100 hours time-in-service: 

(1) For Model BO–105A, BO–105C, BO– 

105S, and BO–105LS A–1 helicopters, 

modify and identify the cyclic stick locking 

device by following the Accomplishment 

Instructions, paragraphs 2.B.1. through 

2.B.2.4 and 2.B.3. through 2.B.3.3., of 

Eurocopter Alert Service Bulletin (ASB) No. 

BO105–40–106, dated December 19, 2008. 

(2) For Model BO–105 LS A–3 helicopters, 

modify and identify the cyclic stick locking 

device by following the Accomplishment 

Instructions, paragraphs 2.B.1.through 

2.B.1.3, of Eurocopter ASB No. ASB–BO 105 

LS 40–10, dated May 8, 2009. 

(3) For Model EC135 P1, EC135 P2, EC135 

P2+, EC135 T1, EC135 T2, and EC135 T2+ 

helicopters, modify and identify the cyclic 

stick cantilever by following the 

Accomplishment Instructions, paragraphs 

3.B. through 3.C., of Eurocopter ASB EC135– 

67A–015, dated April 14, 2008. 

(4) For Model MBB–BK 117 A–1, MBB–BK 

117 A–3, MBB–BK 117 A–4, MBB–BK 117 B– 

1, MBB–BK 117 B–2, and MBB–BK 117 C– 

1 helicopters, modify and identify the cyclic 

stick locking device by following the 

Accomplishment Instructions, paragraphs 

2.B.1. through 2.B.2.2., of Eurocopter ASB 

No. ASB–MBB–BK117–40–113, dated 

December 22, 2008. 

(5) For Model MBB–BK117 C–2 

helicopters, modify and identify the cyclic 

stick cantilever by following the 

Accomplishment Instructions, paragraphs 

3.B. through 3.C., of Eurocopter ASB MBB 

BK117 C–2–67A–008, dated April 14, 2008. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0049, dated March 19, 2010, which 

superseded EASA AD No. 2009–0079, dated 

April 1, 2009; and EASA AD No. 2008–0113, 

dated June 10, 2008. You may view the EASA 

AD at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2012–1305. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710 Main Rotor Control. 

(i) 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 Eurocopter service 

information as applicable to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(i) ASB BO105–40–106, dated December 

19, 2008. 

(ii) ASB–BO 105 LS 40–10, dated May 8, 

2009. 

(iii) ASB EC135–67A–015, dated April 14, 

2008. 

(iv) ASB–MBB–BK117–40–113, dated 

December 22, 2008. 

(v) ASB MBB BK117 C–2–67A–008, dated 

April 14, 2008. 

(3) For Eurocopter Deutschland GmBh 

helicopters service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

http://www.eurocopter.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on May 29, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13473 Filed 6–20–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1330; Directorate 

Identifier 2012–CE–006–AD; Amendment 

39–17470; AD 2013–11–10] 

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 certain 

Cessna Aircraft Company (Cessna) 

(previously COLUMBIA or LANCAIR) 

Models LC40–550FG, LC41–550FG, and 

LC42–550FG airplanes. This AD was 

prompted by reports that during 

maximum braking, if the brakes lock up 

and a skid occurs, a severe oscillatory 

yawing motion or ‘‘wheel walk’’ may 

develop, which could result in further 

significant structural damage to the 

airplane. This AD requires insertions 

into the pilot’s operating handbook 

(POH) and the airplane maintenance 

manuals (AMM) regarding proper use of 

the brakes and inspection of the aft 

fuselage. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective July 26, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 26, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Company, Customer Service, 

P.O. Box 7706, Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax (316) 

517–7271; Internet: 

www.cessnasupport.com. 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: Gary 

Park, Aerospace Engineer, Wichita 

Aircraft Certification Office (ACO), 

FAA, 1801 Airport Road, Wichita, KS 

67209; phone: (316) 946–4123; fax: (316) 

946–4107; email: gary.park@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 


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Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations 37449 

NPRM published in the Federal 

Register on December 21, 2012 (77 FR 

75590). That NPRM proposed to require 

insertions into the pilot’s operating 

handbook (POH) and the airplane 

maintenance manuals (AMM) regarding 

proper use of the brakes and inspection 

of the aft fuselage. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Modify the Landing Gear 

Paul Rene LaChance stated that while 

supportive of the AD, he believes it to 

be too late and does not go far enough. 

He commented that he had experienced 

such an incident himself. Maximum 

braking had occurred. Afterward, the 

airplane was flown for a short flight 

with the pilot unaware of the severe tail 

damage, and the tail almost came off. 

The commenter states we should require 

modification of the airplane with the 

main landing gear oriented vertical 

rather than the current forward tilt. 

We do not agree with this comment. 

The controllability of the aircraft is not 

in question if the pilot reduces brake 

pressure in the event of a wheel walking 

event. The procedures in the AD will 

ensure pilots are aware of appropriate 

actions and what inspections are 

required if such an event occurs. The 

commenter may provide substantiating 

data and apply for an alternative 

method of compliance (AMOC) 

following the procedures in paragraph 

(i) of this AD to implement a design 

modification. 

AD Is Not Necessary and Should Be 

Withdrawn 

Darryl James Taylor, Steven Masters, 

William Paul Boyd, Paul Harrington, 

George Richard Wilhelmsen, Todd 

Thompson, Larry D. Fenwick, and 

Thomas Clare who is President of the 

Cessna Advanced Aircraft Club (CAAC), 

requested we withdraw the NPRM (77 

FR 75590, December 21, 2012) because 

it is unnecessary, does not add to safety, 

and is ineffective. The AD would affect 

726 airplanes, and there have only been 

five occurrences out of thousands of 

landings over the past nine years. The 

commenters do not feel this is 

statistically significant. Since the AD 

comes several years after an isolated 

incident, the AD addresses no real 

safety concern. Appropriate notices 

have already been incorporated in POH 

manuals per Cessna Service Bulletin SB 

10–11–01, dated August 17, 2010. The 

commenters feel it is unlikely that 

additional notes to the POH or placards 

will be an effective solution. 

We do not agree with this comment. 

The wheel walking characteristics are 

highly unusual. We are unaware of any 

other airplane model that has 

experienced such an event. Currently, 

the events are relatively well publicized, 

but they may be forgotten or unknown 

to future pilots without previous 

knowledge about the airplane. Adding 

the changes to the POH and 

maintenance manual and mandating the 

aft fuselage inspection will assure that 

someone does not take off again after an 

event without having the airplane 

inspected. The added changes will also 

help the pilot better know how to 

handle the airplane if the wheel walk 

event does occur. The AD process is the 

only means where the FAA can require 

all owner/operators to incorporate all 

the necessary changes and conduct the 

required inspection. However, owner/ 

operators that have already incorporated 

the POH changes per the Cessna service 

bulletin may receive credit for certain 

actions required by this AD. 

Engineering Solution Needed 

Darryl James Taylor, William Paul 

Boyd, Paul Herrington, George Richard 

Wilhelmsen, and Larry D. Fenwick 

commented that maximum braking is 

considered panic braking where the 

pilot instinctively reacts to an adverse 

condition, and they feel the real issue is 

proper maintenance training. The 

braking issue occurs only when the gear 

bushings have slipped completely out, 

and maintenance shops do not know 

what they are looking at. In which case, 

the solutions in the AD will be 

ineffective. Probably, the landings were 

not made under ideal or normal 

conditions, and the pilots may have 

exceeded operational specifications 

during landing. This issue should have 

an engineering solution such as antilock brakes, which could prevent brake 

lock-up and avoid the adverse 

condition. It would address maximum 

braking, no matter what the cause. The 

anti-lock system would include slotted 

wheels and Hall sensors and change the 

current braking system. The cost would 

be justified because of the reduced risk 

of structural damage. 

We do not agree with this comment. 

Although we would consider a design 

change as an AMOC, we have 

determined that the requirements in this 

AD are sufficient to address the unsafe 

condition. The commenters may 

provide substantiating data and apply 

for an AMOC following the procedures 

in paragraph (i) of this AD to implement 

a modification as an acceptable level of 

safety to address the unsafe condition. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

75590, December 21, 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 75590, 

December 21, 2012). 

Costs of Compliance 

We estimate that this AD affects 726 

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 

Insertion into the POH and the maintenance manuals, and inspection of aft 

fuselage.

4.5 work-hours × $85 per hour = $382.50 Not applicable ........... $382.50 $277,695 

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, 


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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): 

2013–11–10 Cessna Aircraft Company: 

Amendment 39–17470 ; Docket No. 

FAA–2012–1330; Directorate Identifier 

2012–CE–006–AD. 

(a) Effective Date 

This AD is effective July 26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to the following Cessna 

Aircraft Company (previously COLUMBIA or 

LANCAIR) Models LC40–550FG, LC41– 

550FG, and LC42–550FG airplanes that are 

certificated in any category: 

(i) LC40–550FG (Model 300), serial 

numbers 40001 through 40079; 

(ii) LC41–550FG (Model 400), serial 

numbers 41001 through 41108, 41501 

through 41533, 41563 through 41800, and 

411001 through 411161; and 

(iii) LC42–550FG (Model 350), serial 

numbers 42001 through 42084, 42501 

through 42569, and 421001 through 421020. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 5300, Fuselage Structure (General). 

(e) Unsafe Condition 

This AD was prompted by reports that 

during maximum braking, if the brakes lock 

up and a skid occurs, a severe oscillatory 

yawing motion or ‘‘wheel walk’’ may 

develop, which could result in significant 

structural damage to the airplane. We are 

proposing this AD to correct the unsafe 

condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the next 50 hours time-inservice (TIS) after July 26, 2013 (the effective 

date of this AD) or within the next 3 months 

after July 26, 2013 (the effective date of this 

AD), whichever occurs first, incorporate 

figure 1 of paragraph (g)(1) of this AD into 

the applicable Pilot’s Operating Handbook 

(POH)/FAA-approved Airplane Flight 

Manual (AFM), Section 2, Limitations (Other 

Limitations). This may also be done by 

inserting a copy of this AD into the POH/ 

AFM. 

(2) Within the next 50 hours TIS after July 

26, 2013 (the effective date of this AD) or 

within the next 3 months after July 26, 2013 

(the effective date of this AD), whichever 

occurs first, insert a copy of this AD into the 

POH/AFM or incorporate figure 2 of 

paragraph (g)(2) of this AD into the 

applicable POH/AFM at the end of each of 

the following sections: 

(i) Section 4, Normal Procedures 

(Amplified Procedures): Landings, Normal 

Landings; and 

(ii) Section 4, end of paragraph: Short Field 

Landings. 


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(3) Within the next 50 hours TIS after July 

26, 2013 (the effective date of this AD) or 

within the next 3 months after July 26, 2013 

(the effective date of this AD), whichever 

occurs first, incorporate the following Cessna 

Aircraft Company maintenance manual 

revisions for the appropriate model airplane 

as specified in paragraphs (g)(3)(i) through 

(g)(3)(iii) of this AD into your maintenance 

program (maintenance manual). 

(i) For Model LC40–550FG (Model 300): 

Pages 1 through 5, Subject 20–95–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–02, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC40–550FG, 

300MM02, Revision 2, dated July 1, 2012. 

(ii) For Model LC41–550FG (Model 400): 

Pages 1 through 5, Subject 20–90–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–00, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC41–550FG/ 

T240, 400MM02, Revision 2, dated July 1, 

2012. 

(iii) For Model LC42–550FG (Model 350): 

Pages 1 through 5, Subject 20–95–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–02, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC42–550FG, 

350MM02, Revision 2, dated July 1, 2012. 

Note 1 for paragraph (g)(3) of this AD: We 

recommend you replace your current 

maintenance manual in its entirety with the 

updated Cessna Aircraft Company 

Maintenance Manual applicable to your 

model airplane, 300MM02, 350MM02, or 

400MM02, all Revision 2, all dated July 1, 

2012. 

(4) The actions required by paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1)–(4) and 

14 CFR 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(5) At the next annual inspection after July 

26, 2013 (the effective date of this AD) or 

within the next 50 hours TIS after July 26, 

2013 (the effective date of this AD), 

whichever occurs later, and before further 

flight if a severe oscillatory yawing motion as 

described in figure 1 of paragraph (g)(1) of 

this AD has occurred, inspect the aft fuselage 

following the aft fuselage inspection 

procedures for the appropriate model of 

airplane as specified in paragraphs (g)(5)(i) 

through (g)(5)(iii) of this AD. 

(i) For Model LC40–550FG (Model 300): 

Pages 1 through 5, Subject 20–95–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–02, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC40–550FG, 

300MM02, Revision 2, dated July 1, 2012. 

(ii) For Model LC41–550FG (Model 400): 

Pages 1 through 5, Subject 20–90–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–00, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual Model LC41–550FG/ 

T240, 400MM02, Revision 2, dated July 1, 

2012. 

(iii) For Model LC42–550FG (Model 350): 

Pages 1 through 5, Subject 20–95–00, ‘‘Tap 

Testing—Description and Operation’’; pages 

1 through 2, Subject 20–95–02, ‘‘Structural 

Inspections—Description and Operation’’; 

and pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC42–550FG, 

350MM02, Revision 2, dated July 1, 2012. 

(6) If any damaged or suspect areas are 

found during any aft fuselage inspection 

required by paragraph (g)(5) of this AD, 

before further flight, contact Cessna Customer 

Service by phone at (316) 517–5800 or fax at 

(316) 517–7271 for an FAA-approved repair 

and perform the repair. 

(h) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Cessna Aircraft Company released the 

following POH/AFM Temporary Revisions 

via Cessna Service Bulletin SB 10–11–01, 

dated August 17, 2010. Incorporation of the 

applicable document specified in paragraphs 

(h)(i) through (h)(iii) of this AD is considered 

compliance with the POH/AFM change 

requirements in paragraphs (g)(1) and (g)(2) 

of this AD. The applicable POH/AFM 

Temporary Revisions are: 

(i) Cessna Corvalis 300: RA050001–O 

TR03–06, dated August 13, 2010; 

(ii) Cessna Corvalis 350: RB050005–I 

TR08–11 (Garmin G1000-equipped) and 

RB050000–R TR02–05 (Avidyne Entegraequipped), dated August 13, 2010; and 

(iii) Cessna Corvalis 400: RC050005–I 

TR10–13 (Garmin G1000-equipped) and 

RC050002–G TR02–05 (Avidyne Entegraequipped), dated August 13, 2010. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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. 

(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Gary Park, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, KS 67209; phone: (316) 946–4123; 


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37452 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations 

fax: (316) 946–4107; email: 

gary.park@faa.gov. 

(2) Cessna Service Bulletin SB 10–11–01, 

dated August 17, 2010. 

(k) 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) Pages 1 through 5, Subject 20–95–00, 

‘‘Tap Testing—Description and Operation’’; 

of Cessna Aircraft Company Maintenance 

Manual, Model LC40–550FG, 300MM02, 

Revision 2, dated July 1, 2012. 

(ii) Pages 1 through 2, Subject 20–95–02, 

‘‘Structural Inspections—Description and 

Operation’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC40–550FG, 

300MM02, Revision 2, dated July 1, 2012. 

(iii) Pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC40–550FG, 

300MM02, Revision 2, dated July 1, 2012. 

(iv) Pages 1 through 5, Subject 20–90–00, 

‘‘Tap Testing—Description and Operation’’; 

of Cessna Aircraft Company Maintenance 

Manual, Model LC41–550FG/T240, 

400MM02, Revision 2, dated July 1, 2012. 

(v) Pages 1 through 2, Subject 20–95–00, 

‘‘Structural Inspections—Description and 

Operation’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC41–550FG/ 

T240, 400MM02, Revision 2, dated July 1, 

2012. 

(vi) Pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC41–550FG/ 

T240, 400MM02, Revision 2, dated July 1, 

2012. 

(vii) Pages 1 through 5, Subject 20–95–00, 

‘‘Tap Testing—Description and Operation’’; 

of Cessna Aircraft Company Maintenance 

Manual, Model LC42–550FG, 350MM02, 

Revision 2, dated July 1, 2012. 

(viii) Pages 1 through 2, Subject 20–95–02, 

‘‘Structural Inspections—Description and 

Operation’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC42–550FG, 

350MM02, Revision 2, dated July 1, 2012. 

(ix) Pages 501 through 503, Subject 53–70– 

00, ‘‘Fuselage Components—Adjustment/ 

Test’’; of Cessna Aircraft Company 

Maintenance Manual, Model LC42–550FG, 

350MM02, Revision 2, dated July 1, 2012. 

(3) For Cessna Aircraft Company service 

information identified in this AD, contact 

Cessna Aircraft Company, Customer Service, 

P.O. Box 7706, Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax (316) 517– 

7271; Internet: www.cessnasupport.com. 

(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 May 

23, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–14689 Filed 6–20–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30906; Amdt. No. 3541] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective June 21, 

2013. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of June 21, 

2013. 

ADDRESSES: Availability of matter 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169 or, 

4. 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Availability—All SIAPs are available 

online free of charge. Visit nfdc.faa.gov 

to register. Additionally, individual 

SIAP and Takeoff Minimums and ODP 

copies may be obtained from: 

1. FAA Public Inquiry Center (APA– 

200), FAA Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; or 

2. The FAA Regional Office of the 

region in which the affected airport is 

located. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham III, Flight Procedure 

Standards Branch (AFS–420) Flight 

Technologies and Programs Division, 

Flight Standards Service, Federal 

Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082, Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This rule 

amends Title 14, Code of Federal 

Regulations, Part 97 (14 CFR part 97) by 

amending the referenced SIAPs. The 

complete regulatory description of each 

SIAP is listed on the appropriate FAA 

Form 8260, as modified by the National 

Flight Data Center (FDC)/Permanent 

Notice to Airmen (P–NOTAM), and is 

incorporated by reference in the 

amendment under 5 U.S.C. 552(a), 1 

CFR part 51, and § 97.20 of Title 14 of 

the Code of Federal Regulations. 

The large number of SIAPs, their 

complex nature, and the need for a 

special format make their verbatim 

publication in the Federal Register 

expensive and impractical. Further, 

airmen do not use the regulatory text of 

the SIAPs, but refer to their graphic 

depiction on charts printed by 

publishers of aeronautical materials. 

Thus, the advantages of incorporation 

by reference are realized and 

publication of the complete description 

of each SIAP contained in FAA form 

documents is unnecessary. This 

amendment provides the affected CFR 

sections and specifies the types of SIAP 

and the corresponding effective dates. 

This amendment also identifies the 

airport and its location, the procedure 

and the amendment number. 


TKELLEY on DSK3SPTVN1PROD with RULES