81 FR 21250 - Airworthiness Directives; Textron Aviation, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 69 (April 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 69 (April 11, 2016)
| Page Range | 21250-21253 | |
| FR Document | 2016-07798 |
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)] [Rules and Regulations] [Pages 21250-21253] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07798] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5457; Directorate Identifier 2016-CE-008-AD; Amendment 39-18469; AD 2016-07-24] RIN 2120-AA64 Airworthiness Directives; Textron Aviation, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C [[Page 21251]] airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). This AD requires replacement and repetitive inspections of the hardware securing the elevator trim push-pull rod. This AD was prompted by lessons learned in accident investigation support, analysis of past accidents, and NTSB determinations of probable cause. That information indicates that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator tab may jam in a position outside the normal limits of travel. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective April 26, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 26, 2016. We must receive comments on this AD by May 26, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; fax: (316) 517-7271; email: [email protected]; Internet: https://support.cessna.com/custsupt/csupport/newlogin.jsp. You may review this 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5457. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 5457; 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 street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4116; fax: (316) 946-4107; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion This AD was prompted by accident reports on Textron Aviation, Inc. Models T310Q, 310Q, and 402B airplanes. Lessons learned in the accident investigation support, analysis of past accidents, and NTSB determinations of probable cause indicate that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator tab may jam in a position outside the normal limits of travel. This condition, if not corrected, could result in a loss of the ability to control the airplane. We are issuing this AD to correct the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed Textron Aviation, Inc. (Cessna Aircraft Company) Multi- engine Service Bulletin No. MEB-27-02, dated February 29, 2016. The service information describes procedures for replacing the hardware connecting the elevator trim push-pull rod to the elevator trim actuator and elevator trim tab. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires replacement and repetitive inspection of the elevator trim tab push-pull rod connecting hardware. Differences Between the AD and the Service Information Due to the immediate safety of flight condition of this AD action, we are requiring replacement of the hardware within 90 days after the effective date of this AD rather than the potential of up to a year as allowed in the service information. FAA's Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod may result in jamming of the elevator trim tab beyond normal limits, which could result in loss of ability to control the airplane. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA-2016-5457 and Directorate Identifier 2016-CE-008-AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 5,066 airplanes of U.S. registry. We estimate the following costs to comply with this AD: [[Page 21252]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Elevator trim push-pull rod hardware 1 work-hour x $85 per $18.50 $103.50 $524,331 replacement. hour = $85. Repetitive Inspection................. 1 work-hour x $85 per .............. 85 430,610 hour = $85. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. This is the same replacement that is initially required by this AD. We have no way of determining the number of aircraft that might need this repetitive on-condition replacement: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Elevator trim push-pull rod hardware 1 work-hour x $85 per hour = $85 $18.50 $103.50 replacement. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 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): 2016-07-24 Textron Aviation, Inc.: Amendment 39-18469; Docket No. FAA-2016-5457; Directorate Identifier 2016-CE-008-AD. (a) Effective Date This AD is effective April 26, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company), all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 2731, Elevator Tab Control System. (e) Unsafe Condition This AD was prompted by lessons learned in accident investigation support, analysis of past accidents, and NTSB determinations of probable cause. That information confirms that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator tab may jam in a position outside the normal limits of travel and could result in loss of control. We are issuing this AD to correct the unsafe condition on these products. (f) Actions and Compliance Unless already done, do the actions in paragraphs (f)(1) through (f)(3) of this AD within the compliance times specified. (1) Within the next 90 days after April 26, 2016 (the effective date of this AD), replace the elevator trim push-pull rod attachment hardware on the elevator trim actuator and the trim tab ends of the push-pull rod following steps 2 through 5 of the accomplishment instructions in Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin No. MEB-27-02, dated February 29, 2016. (2) Following the replacement required in paragraph (f)(1) of this AD, at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first, repetitively inspect the elevator trim push- pull rod attachment hardware on the elevator trim actuator and the trim tab ends of the push-pull rod, and replace the hardware if necessary before further flight following the Compliance NOTE on page 1 of Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin No. MEB-27-02, dated February 29, 2016. (3) After April 26, 2016 (the effective date of this AD), any time the elevator trim push-pull rod attachment hardware on the elevator trim actuator and/or trim tab ends of the push-pull rod is removed for any reason, discard the old hardware (bolt, nut, washer and cotter pin) and replace with new hardware following steps 3 and/ or step 5 of [[Page 21253]] Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin No. MEB-27-02, dated February 29, 2016. (g) Special Flight Permit Special flight permits are allowed for this AD per 14 CFR 39.23 with the following limitation: Before flight a pre-flight inspection is required of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod. Confirmation of the presence of a castellated nut and cotter pin is required. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita 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 paragraph (i) 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. (i) Related Information For more information about this AD, contact Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946- 4116; fax: (316) 946-4107; email: [email protected]. (j) 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) Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin No. MEB-27-02, dated February 29, 2016. (ii) Reserved. (3) For Textron Aviation, Inc. (Cessna) service information identified in this AD, contact Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; fax: (316) 517-7271; email: [email protected]; Internet: https://support.cessna.com/custsupt/csupport/newlogin.jsp (4) You may view this 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA- 2016-5457. (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 March 30, 2016. Jacqueline Jambor, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07798 Filed 4-8-16; 8:45 am] BILLING CODE 4910-13-P
![21250 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
this cracking by conducting an HFEC (o) Exception to Service Information (ii) Reserved.
inspection, in accordance with the Specification (4) The following service information was
Accomplishment Instructions of Airbus Although Airbus Service Bulletin A300– approved for IBR on October 30, 1997 (62 FR
Service Bulletin A300–57–6044, Revision 04, 57–6044, Revision 04, dated August 19, 2011, 50251, September 25, 1997).
dated August 19, 2011, including Appendix including Appendix 01, Revision 04, dated (i) Airbus Service Bulletin A300–57–6044,
01, Revision 04, dated August 19, 2011, August 19, 2011, specifies to submit Revision 2, dated September 6, 1995,
except as specified in paragraph (o) of this information to Airbus, this AD does not including Appendix 1, Revision 1, dated
AD. If no cracking is confirmed during the require that submission. November 25, 1994. Pages 1 through 8 of this
HFEC inspection, accomplish the applicable document are identified as Revision 2, dated
repetitive inspections required by paragraphs (p) Other FAA AD Provisions September 6, 1995; pages 9 and 10 are
(j) and (l) of this AD at the applicable time The following provisions also apply to this identified as original, dated March 1, 1993.
specified in those paragraphs. AD: Page 1 of Appendix 1 is identified as
(2) If any cracking is found during any (1) Alternative Methods of Compliance Revision 1, dated November 25, 1994; and
HFEC inspection required by paragraph (i), (AMOCs): The Manager, International pages 2 through 6 are identified as original,
(j), or (m)(1) of this AD: Before further flight, Branch, ANM–116, Transport Airplane dated March 1, 1993.
do the applicable actions specified in Directorate, FAA, has the authority to (ii) Reserved.
paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. approve AMOCs for this AD, if requested (5) For service information identified in
(i) If the cracking is 75 mm or less per each using the procedures found in 14 CFR 39.19. this AD, contact Airbus SAS, Airworthiness
rib bay: Before further flight, repair the In accordance with 14 CFR 39.19, send your Office—EAW, 1 Rond Point Maurice
cracking, in accordance with the request to your principal inspector or local Bellonte, 31707 Blagnac Cedex, France;
Accomplishment Instructions of Airbus Flight Standards District Office, as telephone +33 5 61 93 36 96; fax +33 5 61
Service Bulletin A300–57–6044, Revision 04, appropriate. If sending information directly 93 44 51; email account.airworth-
dated August 19, 2011, including Appendix to the International Branch, send it to ATTN: eas@airbus.com; Internet http://
01, Revision 04, dated August 19, 2011, Dan Rodina, Aerospace Engineer, www.airbus.com.
except as specified in paragraph (o) of this International Branch, ANM–116, Transport (6) You may view this service information
AD. Do repetitive detailed inspections of the Airplane Directorate, FAA, 1601 Lind at the FAA, Transport Airplane Directorate,
repaired area thereafter at intervals not to Avenue SW., Renton, WA 98057–3356; 1601 Lind Avenue SW., Renton, WA. For
exceed 50 flight cycles or 110 flight hours, telephone 425–227–2125; fax 425–227–1149. information on the availability of this
whichever occurs first, in accordance with Information may be emailed to: 9-ANM-116- material at the FAA, call 425–227–1221.
the Accomplishment Instructions of Airbus AMOC-REQUESTS@faa.gov. Before using (7) You may view this service information
Service Bulletin A300–57–6044, Revision 04, any approved AMOC, notify your appropriate that is incorporated by reference at the
principal inspector, or lacking a principal National Archives and Records
dated August 19, 2011, including Appendix
inspector, the manager of the local flight Administration (NARA). For information on
01, Revision 04, dated August 19, 2011.
standards district office/certificate holding the availability of this material at NARA, call
Within 250 flight cycles or 550 flight hours,
district office. The AMOC approval letter 202–741–6030, or go to: http://
whichever occurs first after doing the
must specifically reference this AD. www.archives.gov/federal-register/cfr/ibr-
temporary repair, do a permanent repair of
(2) Contacting the Manufacturer: As of the locations.html.
the repaired area, in accordance with the
effective date of this AD, for any requirement
Accomplishment Instructions of Airbus Issued in Renton, Washington, on March
in this AD to obtain corrective actions from
Service Bulletin A300–57–6044, Revision 04, 24, 2016.
a manufacturer, the action must be
dated August 19, 2011, including Appendix Michael Kaszycki,
accomplished using a method approved by
01, Revision 04, dated August 19, 2011. Acting Manager, Transport Airplane
the Manager, International Branch, ANM–
(ii) If the cracking exceeds 75 mm per any 116, Transport Airplane Directorate, FAA; or Directorate, Aircraft Certification Service.
rib bay: Before further flight, install Airbus EASA; or Airbus’s EASA DOA. If approved [FR Doc. 2016–07574 Filed 4–8–16; 8:45 am]
Modification 10089, in accordance with the by the DOA, the approval must include the
Accomplishment Instructions of Airbus BILLING CODE 4910–13–P
DOA-authorized signature.
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix (q) Related Information
01, Revision 04, dated August 19, 2011. Do (1) Refer to Mandatory Continuing DEPARTMENT OF TRANSPORTATION
an LFEC inspection thereafter at the intervals Airworthiness Information (MCAI) EASA
specified in paragraph (l) of this AD. Airworthiness Directive 2013–0221, dated Federal Aviation Administration
(3) If any cracking is found during any September 19, 2013, for related information.
inspection required by this AD at fastener This MCAI may be found in the AD docket 14 CFR Part 39
hole 1A, 1, or 2: Before further flight, repair on the Internet at http://www.regulations.gov
the cracking, in accordance with the [Docket No. FAA–2016–5457; Directorate
by searching for and locating Docket No.
Accomplishment Instructions of Airbus Identifier 2016–CE–008–AD; Amendment
FAA–2015–1426.
Service Bulletin A300–57–6044, Revision 04, 39–18469; AD 2016–07–24]
(2) Service information identified in this
dated August 19, 2011, including Appendix AD that is not incorporated by reference is RIN 2120–AA64
01, Revision 04, dated August 19, 2011. available at the addresses specified in
(4) If any cracking is found during any paragraphs (r)(5) and (r)(6) of this AD. Airworthiness Directives; Textron
LFEC inspection required by paragraph (k) or Aviation, Inc. Airplanes
(l) of this AD: Before further flight, repair (r) Material Incorporated by Reference
using a method approved by the Manager, (1) The Director of the Federal Register AGENCY: Federal Aviation
International Branch, ANM–116, Transport approved the incorporation by reference Administration (FAA), DOT.
Airplane Directorate, FAA; or EASA; or (IBR) of the service information listed in this ACTION: Final rule; request for
Airbus’s EASA DOA. paragraph under 5 U.S.C. 552(a) and 1 CFR comments.
part 51.
(n) Credit for Previous Actions (2) You must use this service information SUMMARY: We are adopting a new
jstallworth on DSK7TPTVN1PROD with RULES
This paragraph provides credit for actions as applicable to do the actions required by airworthiness directive (AD) for all
required by paragraphs (i) through (l) of this this AD, unless this AD specifies otherwise.
AD, if those actions were performed before
Textron Aviation, Inc. Models 310
(3) The following service information was
the effective date of this AD using Airbus approved for IBR on May 16, 2016 through 310R, E310H, E310J, T310P
Service Bulletin A300–57–6044, Revision 03, (i) Airbus Service Bulletin A300–57–6044, through T310R, 310J–1, 320 through
dated April 7, 1999, including Appendix 01, Revision 04, dated August 19, 2011, 320F, 320–1, 335, 340, 340A, 401
Revision 03, dated April 7, 1999, which is including Appendix 01, Revision 04, dated through 401B, 402 through 402C, 411,
not incorporated by reference in this AD. August 19, 2011. 411A, 414, 414A, and 421 through 421C
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ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Elevator trim push-pull rod hardware replace- 1 work-hour × $85 per hour = $85 ................. $18.50 $103.50 $524,331
ment.
Repetitive Inspection ....................................... 1 work-hour × $85 per hour = $85 ................. ........................ 85 430,610
We estimate the following costs to do inspection. This is the same the number of aircraft that might need
any necessary replacements that would replacement that is initially required by this repetitive on-condition
be required based on the results of the this AD. We have no way of determining replacement:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Elevator trim push-pull rod hardware replacement ...... 1 work-hour × $85 per hour = $85 ............................... $18.50 $103.50
Authority for This Rulemaking under the criteria of the Regulatory (d) Subject
Title 49 of the United States Code Flexibility Act. Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
specifies the FAA’s authority to issue List of Subjects in 14 CFR Part 39 Code 2731, Elevator Tab Control System.
rules on aviation safety. Subtitle I,
section 106, describes the authority of Air transportation, Aircraft, Aviation (e) Unsafe Condition
the FAA Administrator. ‘‘Subtitle VII: safety, Incorporation by reference, This AD was prompted by lessons learned
Aviation Programs’’ describes in more Safety. in accident investigation support, analysis of
detail the scope of the Agency’s past accidents, and NTSB determinations of
Adoption of the Amendment probable cause. That information confirms
authority.
that following the loss of the attachment
We are issuing this rulemaking under Accordingly, under the authority hardware connecting the elevator trim tab
the authority described in Subtitle VII, delegated to me by the Administrator, actuator to the elevator trim tab push-pull
Part A, Subpart III, Section 44701: the FAA amends 14 CFR part 39 as rod, the elevator tab may jam in a position
‘‘General requirements.’’ Under that follows: outside the normal limits of travel and could
section, Congress charges the FAA with result in loss of control. We are issuing this
promoting safe flight of civil aircraft in PART 39—AIRWORTHINESS AD to correct the unsafe condition on these
air commerce by prescribing regulations DIRECTIVES products.
for practices, methods, and procedures (f) Actions and Compliance
the Administrator finds necessary for ■ 1. The authority citation for part 39 Unless already done, do the actions in
safety in air commerce. This regulation continues to read as follows: paragraphs (f)(1) through (f)(3) of this AD
is within the scope of that authority within the compliance times specified.
Authority: 49 U.S.C. 106(g), 40113, 44701.
because it addresses an unsafe condition (1) Within the next 90 days after April 26,
that is likely to exist or develop on § 39.13 [Amended] 2016 (the effective date of this AD), replace
products identified in this rulemaking the elevator trim push-pull rod attachment
■ 2. The FAA amends § 39.13 by adding hardware on the elevator trim actuator and
action.
the trim tab ends of the push-pull rod
the following new airworthiness
Regulatory Findings following steps 2 through 5 of the
directive (AD): accomplishment instructions in Textron
This AD will not have federalism 2016–07–24 Textron Aviation, Inc.: Aviation, Inc. (Cessna) Multi-engine Service
implications under Executive Order Amendment 39–18469; Docket No. Bulletin No. MEB–27–02, dated February 29,
13132. This AD will not have a FAA–2016–5457; Directorate Identifier 2016.
substantial direct effect on the States, on 2016–CE–008–AD. (2) Following the replacement required in
the relationship between the national paragraph (f)(1) of this AD, at intervals not
government and the States, or on the (a) Effective Date to exceed 100 hours TIS or 12 months,
distribution of power and This AD is effective April 26, 2016. whichever occurs first, repetitively inspect
the elevator trim push-pull rod attachment
responsibilities among the various (b) Affected ADs hardware on the elevator trim actuator and
levels of government. the trim tab ends of the push-pull rod, and
For the reasons discussed above, I None.
replace the hardware if necessary before
certify that this AD: (c) Applicability further flight following the Compliance
(1) Is not a ‘‘significant regulatory This AD applies to Textron Aviation, Inc. NOTE on page 1 of Textron Aviation, Inc.
action’’ under Executive Order 12866, (Cessna) Multi-engine Service Bulletin No.
Models 310 through 310R, E310H, E310J,
(2) Is not a ‘‘significant rule’’ under MEB–27–02, dated February 29, 2016.
T310P through T310R, 310J–1, 320 through
jstallworth on DSK7TPTVN1PROD with RULES
DOT Regulatory Policies and Procedures (3) After April 26, 2016 (the effective date
320F, 320–1, 335, 340, 340A, 401 through of this AD), any time the elevator trim push-
(44 FR 11034, February 26, 1979), 401B, 402 through 402C, 411, 411A, 414, pull rod attachment hardware on the elevator
(3) Will not affect intrastate aviation 414A, and 421 through 421C airplanes (type trim actuator and/or trim tab ends of the
in Alaska, and certificates 3A10, 3A25, and A7CE push-pull rod is removed for any reason,
(4) Will not have a significant previously held by Cessna Aircraft discard the old hardware (bolt, nut, washer
economic impact, positive or negative, Company), all serial numbers, certificated in and cotter pin) and replace with new
on a substantial number of small entities any category. hardware following steps 3 and/or step 5 of
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![Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21253
Textron Aviation, Inc. (Cessna) Multi-engine www.archives.gov/federal-register/cfr/ibr- • Hand Delivery: U.S. Department of
Service Bulletin No. MEB–27–02, dated locations.html. Transportation, Docket Operations, M–
February 29, 2016. Issued in Kansas City, Missouri, on March 30, West Building Ground Floor, Room
(g) Special Flight Permit 30, 2016. W12–140, 1200 New Jersey Avenue SE.,
Special flight permits are allowed for this Jacqueline Jambor, Washington, DC 20590, between 9 a.m.
AD per 14 CFR 39.23 with the following Acting Manager, Small Airplane Directorate, and 5 p.m., Monday through Friday,
limitation: Before flight a pre-flight Aircraft Certification Service. except Federal holidays.
inspection is required of the attachment [FR Doc. 2016–07798 Filed 4–8–16; 8:45 am] For service information identified in
hardware connecting the elevator trim tab BILLING CODE 4910–13–P
this final rule, contact Boeing
actuator to the elevator trim tab push-pull Commercial Airplanes, Attention: Data
rod. Confirmation of the presence of a & Services Management, 3855
castellated nut and cotter pin is required. DEPARTMENT OF TRANSPORTATION Lakewood Boulevard, MC D800–0019,
(h) Alternative Methods of Compliance Long Beach, CA 90846–0001; telephone
(AMOCs) Federal Aviation Administration 206–544–5000, extension 2; fax 206–
(1) The Manager, Wichita ACO, FAA, has
766–5683; Internet https://
the authority to approve AMOCs for this AD, 14 CFR Part 39 www.myboeingfleet.com. You may view
if requested using the procedures found in 14 [Docket No. FAA–2016–5458; Directorate
this referenced service information at
CFR 39.19. In accordance with 14 CFR 39.19, Identifier 2016–NM–027–AD; Amendment the FAA, Transport Airplane
send your request to your principal inspector 39–18473; AD 2016–07–28] Directorate, 1601 Lind Avenue SW.,
or local Flight Standards District Office, as Renton, WA. For information on the
appropriate. If sending information directly RIN 2120–AA64 availability of this material at the FAA,
to the manager of the ACO, send it to the call 425–227–1221. It is also available
attention of the person identified in Airworthiness Directives; The Boeing
Company Airplanes on the Internet at http://
paragraph (i) of this AD. www.regulations.gov by searching for
(2) Before using any approved AMOC, AGENCY: Federal Aviation and locating Docket No. FAA–2016–
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
Administration (FAA), DOT. 5458.
of the local flight standards district office/ ACTION: Final rule; request for
Examining the AD Docket
certificate holding district office. comments.
You may examine the AD docket on
(i) Related Information SUMMARY: We are adopting a new the Internet at http://
For more information about this AD, airworthiness directive (AD) for all The www.regulations.gov by searching for
contact Adam Hein, Aerospace Engineer, Boeing Company Model DC–9–81 (MD– and locating Docket No. FAA–2016–
Wichita Aircraft Certification Office, FAA, 81), DC–9–82 (MD–82), DC–9–83 (MD– 5458; or in person at the Docket
1801 S. Airport Road, Room 100, Wichita, 83), and DC–9–87 (MD–87) airplanes, Management Facility between 9 a.m.
Kansas 67209; phone: (316) 946–4116; fax: and Model MD–88 airplanes. This AD and 5 p.m., Monday through Friday,
(316) 946–4107; email: adam.hein@faa.gov. requires repetitive eddy current high except Federal holidays. The AD docket
(j) Material Incorporated by Reference frequency (ETHF) inspections for any contains this AD, the regulatory
(1) The Director of the Federal Register cracking in the left and right side center evaluation, any comments received, and
approved the incorporation by reference wing lower skin, and corrective actions other information. The street address for
(IBR) of the service information listed in this if necessary. This AD was prompted by the Docket Office (phone: 800–647–
paragraph under 5 U.S.C. 552(a) and 1 CFR reports of cracking at certain stringers, 5527) is in the ADDRESSES section.
part 51. associated end fittings, and skins in the Comments will be available in the AD
(2) You must use this service information center wing fuel tank where the docket shortly after receipt.
as applicable to do the actions required by stringers meet the end fittings. We are FOR FURTHER INFORMATION CONTACT:
this AD, unless the AD specifies otherwise.
(i) Textron Aviation, Inc. (Cessna) Multi-
issuing this AD to detect and correct Haytham Alaidy, Aerospace Engineer,
engine Service Bulletin No. MEB–27–02, cracking in the center wing lower skin. Airframe Branch, ANM–120L, FAA, Los
dated February 29, 2016. Such cracking could cause structural Angeles Aircraft Certification Office
(ii) Reserved. failure of the wings. (ACO), 3960 Paramount Boulevard,
(3) For Textron Aviation, Inc. (Cessna) DATES: This AD is effective April 26, Lakewood, CA 90712–4137; phone:
service information identified in this AD, 2016. 562–627–5224; fax: 562–627–5210;
contact Textron Aviation Customer Service, The Director of the Federal Register email: haytham.alaidy@faa.gov.
P.O. Box 7706, Wichita, Kansas 67277; approved the incorporation by reference SUPPLEMENTARY INFORMATION:
telephone: (316) 517–5800; fax: (316) 517–
of a certain publication listed in this AD
7271; email: customercare@ Discussion
cessna.textron.com; Internet: https:// as of April 26, 2016.
support.cessna.com/custsupt/csupport/ We must receive comments on this We have received reports of cracks at
newlogin.jsp AD by May 26, 2016. stringers S–15, S–16, or S–17, associated
(4) You may view this service information ADDRESSES: You may send comments, end fittings, and skins in the center
at the FAA, Small Airplane Directorate, 901 using the procedures found in 14 CFR wing fuel tank where the stringers meet
Locust, Kansas City, Missouri 64106. For 11.43 and 11.45, by any of the following the end fittings near Xcw=13 and
information on the availability of this methods: Xcw=15. If stringer S–15, S–16, or S–17
material at the FAA, call (816) 329–4148. It • Federal eRulemaking Portal: Go to is cracked in this area and there is a
is also available on the Internet at http:// http://www.regulations.gov. Follow the crack in the skin adjacent to the stringer
jstallworth on DSK7TPTVN1PROD with RULES
www.regulations.gov by searching for and crack, the skin crack could grow to a
locating Docket No. FAA–2016–5457.
instructions for submitting comments.
(5) You may view this service information
• Fax: 202–493–2251. critical length before it can be found by
that is incorporated by reference at the • Mail: U.S. Department of routine maintenance inspections. This
National Archives and Records Transportation, Docket Operations, M– condition, if not corrected, could result
Administration (NARA). For information on 30, West Building Ground Floor, Room in structural failure of the wings. We are
the availability of this material at NARA, call W12–140, 1200 New Jersey Avenue SE., issuing this AD to correct the unsafe
202–741–6030, or go to: http:// Washington, DC 20590. condition on these products.
VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1](https://thefederalregister.org/doc/81_FR_21319/page/4.svg)
Document Created: 2016-04-09 00:11:17
Document Modified: 2016-04-09 00:11:17
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective April 26, 2016. | |
| Contact | Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4116; fax: (316) 946-4107; email: [email protected] | |
| FR Citation | 81 FR 21250 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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