Airworthiness Directives; Cessna Aircraft Company Airplanes, 37448-37452 [2013-14689]

Download as PDF 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. TKELLEY on DSK3SPTVN1PROD with RULES 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. 16:03 Jun 20, 2013 (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 (g) Additional Information VerDate Mar<15>2010 (h) Subject Joint Aircraft Service Component (JASC) Code: 6710 Main Rotor Control. Jkt 229001 Airworthiness Directives; Cessna Aircraft Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 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 E:\FR\FM\21JNR1.SGM 21JNR1 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations 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 37449 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 Cost per product TKELLEY on DSK3SPTVN1PROD with RULES Action Labor cost Parts cost Insertion into the POH and the maintenance manuals, and inspection of aft fuselage. 4.5 work-hours × $85 per hour = $382.50 Not applicable ........... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Mar<15>2010 16:03 Jun 20, 2013 Jkt 229001 section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 $382.50 Cost on U.S. operators $277,695 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\21JNR1.SGM 21JNR1 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. 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 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. TKELLEY on DSK3SPTVN1PROD with RULES (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 VerDate Mar<15>2010 16:03 Jun 20, 2013 Jkt 229001 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: 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: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (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. (i) Section 4, Normal Procedures (Amplified Procedures): Landings, Normal Landings; and (ii) Section 4, end of paragraph: Short Field Landings. E:\FR\FM\21JNR1.SGM 21JNR1 ER21JN13.000</GPH> 37450 (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 VerDate Mar<15>2010 16:03 Jun 20, 2013 Jkt 229001 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 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 37451 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; E:\FR\FM\21JNR1.SGM 21JNR1 ER21JN13.001</GPH> TKELLEY on DSK3SPTVN1PROD with RULES Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations 37452 Federal Register / Vol. 78, No. 120 / Friday, June 21, 2013 / Rules and Regulations TKELLEY on DSK3SPTVN1PROD with RULES fax: (316) 946–4107; email: gary.park@faa.gov. (2) Cessna Service Bulletin SB 10–11–01, dated August 17, 2010. the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (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 Issued in Kansas City, Missouri, on May 23, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. VerDate Mar<15>2010 16:03 Jun 20, 2013 Jkt 229001 [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 FOR FURTHER INFORMATION CONTACT: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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; SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 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. 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. E:\FR\FM\21JNR1.SGM 21JNR1

Agencies

[Federal Register Volume 78, Number 120 (Friday, June 21, 2013)]
[Rules and Regulations]
[Pages 37448-37452]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-14689]


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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.

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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

[[Page 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 anti-
lock 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                  Labor cost              Parts cost               product        operators
----------------------------------------------------------------------------------------------------------------
Insertion into the POH and the   4.5 work-hours x   Not applicable..............         $382.50        $277,695
 maintenance manuals, and         $85 per hour =
 inspection of aft fuselage.      $382.50.
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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,

[[Page 37450]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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-in-service (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.
[GRAPHIC] [TIFF OMITTED] TR21JN13.000

    (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.

[[Page 37451]]

[GRAPHIC] [TIFF OMITTED] TR21JN13.001

    (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 Entegra-equipped), dated 
August 13, 2010; and
    (iii) Cessna Corvalis 400: RC050005-I TR10-13 (Garmin G1000-
equipped) and RC050002-G TR02-05 (Avidyne Entegra-equipped), 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;

[[Page 37452]]

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/ibr-locations.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