## 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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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 havean 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:



### E STIMATED 

### C OSTS

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,


## 37450 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations

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.


## 37451 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations

(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) andRB050000–R TR02–05 (Avidyne Entegraequipped), dated August 13, 2010; and

(iii) Cessna Corvalis 400: RC050005–I TR10–13 (Garmin G1000-equipped) andRC050002–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;


## 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.