81 FR 72505 - Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 203 (October 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 203 (October 20, 2016)
| Page Range | 72505-72507 | |
| FR Document | 2016-24860 |
[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)] [Rules and Regulations] [Pages 72505-72507] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-24860] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD; Amendment 39-18684; AD 2016-21-03] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model MBB-BK 117 C-2 helicopters with certain duplex trim actuators installed. This AD requires repetitively inspecting the lateral and longitudinal trim actuator output levers for correct torque of the nuts. This AD was prompted by a design review that indicated the attachment screws can become loose under certain circumstances. These actions are intended to prevent the loss of an attachment screw, which could result in movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of helicopter control. DATES: This AD is effective November 25, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641- 3775; or at http://www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket [[Page 72506]] Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion On August 18, 2014, at 79 FR 48696, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator, part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001, installed. The NPRM proposed to require repetitively inspecting the lateral and longitudinal trim actuator output levers for correct torque of the nuts. The proposed requirements were intended to prevent a loose attachment screw, which could result in movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of helicopter control. The NPRM was prompted by AD No. 2013-0182, dated August 12, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator, P/N 418-00878-050 or P/N 418-00878-051, or with a longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878- 001. EASA advises that under unfavorable circumstances, a total loss of the trim actuator output lever attachment screw could lead to a restriction of the lateral and longitudinal control range. According to EASA, without the attachment screw, the output lever can move in the axial direction. This condition, if not detected, could cause the bolt that connects the control rod to the output lever to make contact with actuator housing, possibly resulting in reduced control of the helicopter. To prevent this condition, EASA requires an initial torque check of the lateral and longitudinal trim actuator output lever attachment screws, the application of a torque marking, and repetitive inspections for correct torque thereafter. The EASA AD's requirements are considered an interim solution, pending a terminating modification. Since the issuance of EASA AD No. 2013-0182, Eurocopter Deutschland GmbH has changed its name to Airbus Helicopters Deutschland GmbH. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (79 FR 48696, August 18, 2014). FAA's Determination These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action because Airbus Helicopters is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved and available, we might consider additional rulemaking. Related Service Information We reviewed Eurocopter (now Airbus Helicopters) Alert Service Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013 (ASB), which advises of a design review that showed that a loss of the attachment screw of the trim actuator output lever could restrict the lateral and longitudinal control range. The ASB consequently calls for an initial torque check and application of torque markings of the self- locking nuts, and subsequent repetitive inspections to maintain the proper torque. Costs of Compliance We estimate that this AD affects 100 helicopters of U.S. Registry and that labor costs average $85 per work-hour. Based on these estimates, we expect the following costs:Applying torque and torque marking to the lateral and longitudinal trim actuator output levers requires 1 work-hour for a labor cost of $85. No parts are needed, so the cost for the U.S. fleet totals $8,500. Visually inspecting for correct torque requires 0.5 work- hour for a labor cost of about $43. No parts are needed, so the total cost for the U.S. fleet is $4,300 per inspection cycle. 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 helicopters 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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, [[Page 72507]] 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): 2016-21-03 Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters: Amendment 39-18684; Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD. (a) Applicability This AD applies to Airbus Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator, part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as loss of a trim actuator output lever attachment screw. This condition could result in movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective November 25, 2016. (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 (1) Within 300 hours time-in-service (TIS), apply a torque of 31.0 inch-pounds (3.5 Nm) to the self-locking nut (nut) on each lateral and longitudinal trim actuator output lever and apply a torque marking between the nut and the screw. (2) Thereafter at intervals not to exceed 400 hours TIS, visually inspect each nut on each lateral and longitudinal trim actuator output lever to determine whether the torque is at 31.0 inch-pounds (3.5 Nm). If the torque is not at 31.0 inch-pounds, apply a torque of 31.0 inch-pounds (3.5 Nm), remove the previous torque marking, and apply a new torque marking between the nut and the screw. (3) Do not install a lateral duplex trim actuator, part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001, on any helicopter unless each nut has been inspected for proper torque in accordance with the requirements of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information (1) Eurocopter Alert Service Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641- 3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in the European Aviation Agency (EASA) AD No. 2013-0182, dated August 12, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0578. (h) Subject Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft Flight Control. Issued in Fort Worth, Texas, on October 5, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-24860 Filed 10-19-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72505
compact fluorescent lamps, or integrated LED 3.3. For single base OLED and non- rated input voltage. For non-integrated LED
lamps. integrated LED lamps, position a lamp in lamps, operate the lamp at the manufacturer-
2. Definitions: either the base-up and base-down orientation declared input voltage and current.
Measured initial input power means the throughout testing. Test an equal number of 3.5. Operate the lamp at the maximum
input power to the lamp, measured after the lamps in the sample in the base-up and base- input power. If multiple modes occur at the
lamp is stabilized and seasoned (if down orientations, except that, if the
applicable), and expressed in watts (W). manufacturer restricts the orientation, test all same maximum input power (such as
Measured initial lumen output means the of the units in the sample in the variable CCT or CRI), the manufacturer may
lumen output of the lamp, measured after the manufacturer-specified orientation. For select any of these modes for testing;
lamp is stabilized and seasoned (if double base OLED and non-integrated LED however, all measurements must be taken at
applicable), and expressed in lumens (lm). lamps, test all units in the horizontal the same selected mode. The manufacturer
Power factor means the measured initial orientation except that, if the manufacturer must indicate in the test report which mode
input power (watts) divided by the product restricts the orientation, test all of the units was selected for testing and include detail
of the input voltage (volts) and the input in the sample in the manufacturer-specified such that another laboratory could operate
current (amps) measured at the same time as orientation.
the lamp in the same mode.
the initial input power. 3.4. Operate the lamp at the rated voltage
3. Active Mode Test Procedures throughout testing. For lamps with multiple 3.6. To measure initial lumen output, input
3.1. Take measurements at full light rated voltages including 120 volts, operate power, input voltage, and input current use
output. the lamp at 120 volts. If a lamp is not rated the test procedures in the table in this
3.2. Do not use a goniophotometer. for 120 volts, operate the lamp at the highest section.
TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES
Lamp type Referenced test procedure
General service incandescent lamps ....................................................... Appendix R to subpart B of 10 CFR part 430.
Compact fluorescent lamps ...................................................................... Appendix W to subpart B of 10 CFR part 430.
Integrated LED lamps ............................................................................... Appendix BB to subpart B of 10 CFR part 430.
Other incandescent lamps that are not reflector lamps ........................... IES LM–45–15, sections 4–6, and section 7.1.*
Other incandescent lamps that are reflector lamps ................................. IES LM–20–13, sections 4–6, and section 8.*
Other fluorescent lamps ........................................................................... IES LM–9–09–DD, sections 4–6, and section 7.5.*
OLED lamps ............................................................................................. IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.*
Non-integrated LED lamps ....................................................................... IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.*
* Incorporated by reference, see § 430.3.
3.7. Determine initial lamp efficacy by DEPARTMENT OF TRANSPORTATION movement of the output lever in an
dividing the measured initial lumen output axial direction, contact of a bolt
(lumens) by the measured initial input power Federal Aviation Administration connecting the control rod to an output
(watts). lever with the actuator housing, and
3.8. Determine power factor by dividing 14 CFR Part 39 subsequent loss of helicopter control.
the measured initial input power (watts) by
[Docket No. FAA–2014–0578; Directorate DATES: This AD is effective November
the product of the measured input voltage
(volts) and measured input current (amps). Identifier 2013–SW–048–AD; Amendment 25, 2016.
4. Standby Mode Test Procedure 39–18684; AD 2016–21–03] ADDRESSES: For service information
4.1. Measure standby mode power only for RIN 2120–AA64 identified in this final rule, contact
lamps that are capable of standby mode Airbus Helicopters, Inc., 2701 N. Forum
operation. Airworthiness Directives; Airbus Drive, Grand Prairie, TX 75052;
4.2. Maintain lamp orientation as specified Helicopters Deutschland GmbH telephone (972) 641–0000 or (800) 232–
in section 3.3 of this appendix. (Previously Eurocopter Deutschland 0323; fax (972) 641–3775; or at http://
4.3. Connect the lamp to the manufacturer- www.airbushelicopters.com/techpub.
GmbH) (Airbus Helicopters)
specified wireless control network (if You may review the referenced service
applicable) and configure the lamp in
Helicopters
information at the FAA, Office of the
standby mode by sending a signal to the lamp AGENCY: Federal Aviation Regional Counsel, Southwest Region,
instructing it to have zero light output. Lamp Administration (FAA), DOT. 10101 Hillwood Pkwy, Room 6N–321,
must remain connected to the network
throughout testing.
ACTION: Final rule. Fort Worth, TX 76177.
4.4. Operate the lamp at the rated voltage SUMMARY: We are adopting a new Examining the AD Docket
throughout testing. For lamps with multiple
airworthiness directive (AD) for Airbus You may examine the AD docket on
rated voltages including 120 volts, operate
the lamp at 120 volts. If a lamp is not rated
Helicopters Model MBB–BK 117 C–2 the Internet at http://
for 120 volts, operate the lamp at the highest helicopters with certain duplex trim www.regulations.gov or in person at the
rated input voltage. actuators installed. This AD requires Docket Operations Office between 9
4.5. Stabilize the lamp prior to repetitively inspecting the lateral and a.m. and 5 p.m., Monday through
asabaliauskas on DSK3SPTVN1PROD with RULES
measurement as specified in section 5 of IEC longitudinal trim actuator output levers Friday, except Federal holidays. The AD
62301–DD (incorporated by reference; see for correct torque of the nuts. This AD docket contains this AD, the European
§ 430.3). was prompted by a design review that Aviation Safety Agency (EASA) AD, the
4.6. Measure the standby mode power in indicated the attachment screws can economic evaluation, any comments
watts as specified in section 5 of IEC 62301– become loose under certain received, and other information. The
DD (incorporated by reference; see § 430.3). circumstances. These actions are street address for the Docket Operations
[FR Doc. 2016–25180 Filed 10–19–16; 8:45 am] intended to prevent the loss of an Office (phone: 800–647–5527) is U.S.
BILLING CODE 6450–01–P attachment screw, which could result in Department of Transportation, Docket
VerDate Sep<11>2014 15:55 Oct 19, 2016 Jkt 241001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\20OCR1.SGM 20OCR1](https://thefederalregister.org/doc/81_FR_72708/page/1.svg)
![Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72507
the FAA amends 14 CFR part 39 as (f) Alternative Methods of Compliance SUMMARY: We are superseding
follows: (AMOCs) Airworthiness Directive (AD) 2012–20–
(1) The Manager, Safety Management 07 for certain Airbus Model A318,
PART 39—AIRWORTHINESS Group, FAA, may approve AMOCs for this A319, A320, and A321 series airplanes.
DIRECTIVES AD. Send your proposal to: Matt Wilbanks, AD 2012–20–07 required revising the
Aviation Safety Engineer, Regulations and Airworthiness Limitations section (ALS)
■ 1. The authority citation for part 39 Policy Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Room 6N–321, Fort
of the Instructions for Continued
continues to read as follows:
Worth, TX 76177; telephone (817) 222–5110; Airworthiness (ICA) to incorporate new
Authority: 49 U.S.C. 106(g), 40113, 44701. limitations for fuel tank systems, and
email 9-ASW-FTW-AMOC-Requests@faa.gov.
§ 39.13 [Amended] (2) For operations conducted under a 14 revising the maintenance program to
CFR part 119 operating certificate or under incorporate revised fuel maintenance
■ 2. The FAA amends § 39.13 by adding 14 CFR part 91, subpart K, we suggest that and inspection tasks. This new AD
the following new airworthiness you notify your principal inspector, or requires revising the maintenance or
directive (AD): lacking a principal inspector, the manager of inspection program to incorporate
2016–21–03 Airbus Helicopters the local flight standards district office or revised fuel airworthiness limitations.
Deutschland GmbH (Previously certificate holding district office, before
operating any aircraft complying with this
This AD was prompted by Airbus
Eurocopter Deutschland GmbH) (Airbus issuing more restrictive maintenance
Helicopters) Helicopters: Amendment AD through an AMOC.
requirements and/or airworthiness
39–18684; Docket No. FAA–2014–0578; (g) Additional Information
Directorate Identifier 2013–SW–048–AD.
limitations. We are issuing this AD to
(1) Eurocopter Alert Service Bulletin MBB– prevent the potential of ignition sources
(a) Applicability BK117 C–2–67A–020, Revision 0, dated June inside fuel tanks, which, in combination
This AD applies to Airbus Helicopters 18, 2013, which is not incorporated by with flammable fuel vapors, could result
Model MBB–BK 117 C–2 helicopters with a reference, contains additional information in a fuel tank explosion and consequent
lateral duplex trim actuator, part number (P/ about the subject of this AD. For service
information identified in this final rule,
loss of the airplane.
N) 418–00878–050 or P/N 418–00878–051, or
contact Airbus Helicopters, Inc., 2701 N. DATES: This AD is effective November
a longitudinal duplex trim actuator, P/N 418–
00878–000 or P/N 418–00878–001, installed, Forum Drive, Grand Prairie, TX 75052; 25, 2016.
certificated in any category. telephone (972) 641–0000 or (800) 232–0323; The Director of the Federal Register
fax (972) 641–3775; or at http:// approved the incorporation by reference
(b) Unsafe Condition www.airbushelicopters.com/techpub. You of a certain publication listed in this AD
This AD defines the unsafe condition as may review a copy of the service information as of November 25, 2016.
loss of a trim actuator output lever at the FAA, Office of the Regional Counsel,
The Director of the Federal Register
attachment screw. This condition could Southwest Region, 10101 Hillwood Parkway,
Room 6N–321, Fort Worth, TX 76177. approved the incorporation by reference
result in movement of the output lever in an
axial direction, contact of a bolt connecting (2) The subject of this AD is addressed in of a certain other publication listed in
the control rod to an output lever with the the European Aviation Agency (EASA) AD this AD as of November 21, 2012 (77 FR
actuator housing, and subsequent loss of No. 2013–0182, dated August 12, 2013. You 63716, October 17, 2012).
control of the helicopter. may view the EASA AD on the Internet at The Director of the Federal Register
http://www.regulations.gov in Docket No. approved the incorporation by reference
(c) Effective Date FAA–2014–0578. of a certain other publication listed in
This AD becomes effective November 25, this AD as of December 14, 2009 (74 FR
2016. (h) Subject
Joint Aircraft Service Component (JASC) 62219, November 27, 2009).
(d) Compliance Code: 6700, Rotorcraft Flight Control. The Director of the Federal Register
You are responsible for performing each approved the incorporation by reference
Issued in Fort Worth, Texas, on October 5,
action required by this AD within the of a certain other publication listed in
specified compliance time unless it has 2016.
this AD as of August 28, 2007 (72 FR
already been accomplished prior to that time. Lance T. Gant,
40222, July 24, 2007).
Manager, Rotorcraft Directorate, Aircraft
(e) Required Actions ADDRESSES: For service information
Certification Service.
(1) Within 300 hours time-in-service (TIS), identified in this final rule, contact
[FR Doc. 2016–24860 Filed 10–19–16; 8:45 am]
apply a torque of 31.0 inch-pounds (3.5 Nm) Airbus, Airworthiness Office—EIAS, 1
BILLING CODE 4910–13–P
to the self-locking nut (nut) on each lateral Rond Point Maurice Bellonte, 31707
and longitudinal trim actuator output lever Blagnac Cedex, France; telephone +33 5
and apply a torque marking between the nut 61 93 36 96; fax +33 5 61 93 44 51; email
and the screw. DEPARTMENT OF TRANSPORTATION
account.airworth-eas@airbus.com;
(2) Thereafter at intervals not to exceed 400
Federal Aviation Administration Internet http://www.airbus.com. You
hours TIS, visually inspect each nut on each
lateral and longitudinal trim actuator output may view this referenced service
lever to determine whether the torque is at 14 CFR Part 39 information at the FAA, Transport
31.0 inch-pounds (3.5 Nm). If the torque is Airplane Directorate, 1601 Lind Avenue
not at 31.0 inch-pounds, apply a torque of [Docket No. FAA–2016–5589; Directorate SW., Renton, WA. For information on
Identifier 2014–NM–252–AD; Amendment
31.0 inch-pounds (3.5 Nm), remove the the availability of this material at the
previous torque marking, and apply a new 39–18678; AD 2016–20–12]
FAA, call 425–227–1221. It is also
torque marking between the nut and the RIN 2120–AA64 available on the Internet at http://
asabaliauskas on DSK3SPTVN1PROD with RULES
screw. www.regulations.gov by searching for
(3) Do not install a lateral duplex trim Airworthiness Directives; Airbus and locating Docket No. FAA–2016–
actuator, part number (P/N) 418–00878–050 Airplanes
or P/N 418–00878–051, or a longitudinal 5589.
duplex trim actuator, P/N 418–00878–000 or AGENCY: Federal Aviation Examining the AD Docket
P/N 418–00878–001, on any helicopter Administration (FAA), Department of
unless each nut has been inspected for Transportation (DOT). You may examine the AD docket on
proper torque in accordance with the the Internet at http://
ACTION: Final rule.
requirements of this AD. www.regulations.gov by searching for
VerDate Sep<11>2014 15:55 Oct 19, 2016 Jkt 241001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\20OCR1.SGM 20OCR1](https://thefederalregister.org/doc/81_FR_72708/page/3.svg)
Document Created: 2016-10-21 09:59:18
Document Modified: 2016-10-21 09:59:18
| 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. | |
| Dates | This AD is effective November 25, 2016. | |
| Contact | Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 81 FR 72505 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR