80 FR 60030 - Airworthiness Directives; Airbus Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 192 (October 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 192 (October 5, 2015)
| Page Range | 60030-60033 | |
| FR Document | 2015-25217 |
[Federal Register Volume 80, Number 192 (Monday, October 5, 2015)] [Rules and Regulations] [Pages 60030-60033] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-25217] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3877; Directorate Identifier 2015-SW-039-AD; Amendment 39-18284; AD 2015-18-51] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain tail rotor (T/R) blades, replacing the set of T/R blades if there is damage, deactivating the rotor de-icing system, revising the rotorcraft flight manual (RFM), and installing a placard. This AD is prompted by a report of a T/R de-icing system power supply box stuck in a ``closed'' position providing an uncontrolled and un-annunciated power supply to the system. These actions are intended to detect and prevent structural damage to the T/R blades caused by overheating, and subsequent loss of control of the helicopter. DATES: This AD becomes effective October 20, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015-18-51, issued on September 11, 2015, which contains the requirements of this AD. We must receive comments on this AD by December 4, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. [[Page 60031]] 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-2015- 3877; 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 (telephone 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact Airbus Helicopters, 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. FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion On September 11, 2015, we issued Emergency AD 2015-18-51 to correct an unsafe condition for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters with T/R de-icing installation unit part number (P/N) 204ZP01Y01 and T/R blade P/N 332A12-0055-XX (where XX is any dash number) installed. Emergency AD 2015-18-51 requires inspecting each T/R blade, replacing the set of T/R blades if there is damage, deactivating the rotor de-icing system, revising the RFM, and installing a placard. Emergency AD 2015-18-51 was sent previously to all known U.S. owners and operators of these helicopters and was prompted by a report of a T/R de-icing system power supply box stuck in a ``closed'' position providing an uncontrolled and un-annunciated power supply to the system. The T/R de-icing system is part of the entire rotor de-icing system. Emergency AD 2015-18-51 was prompted by AD No. 2015-0153-E, dated July 24, 2015, 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 AS332 C, AS332C1, AS332L, and AS332L1 helicopters, equipped with T/R de-icing installation unit P/N 204ZP01Y01 and T/R blade P/N 332A12-0055-XX (where XX represents any dash number). EASA advises of a report of a T/R blade that was overheated and damaged after application of alternating current (AC) from a ground power unit (GPU) following a flight during which the de- icing system was used. Subsequent analysis determined failure of the power supply box stuck in the ``closed'' position caused the uncontrolled power supply to the rotor blade de-icing system and subsequent damage. EASA also states that its AD is considered an interim action and further AD action may follow. FAA's Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, 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 the EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information Airbus Helicopters issued Alert Service Bulletin No. AS332- 05.01.02, Revision 0, dated July 22, 2015 (ASB), which specifies, before each flight and before starting at least one engine, if the applicable helicopter has been supplied external 115V/400Hz AC GPU with the rotor stationary or if the de-icing system has been used or tested using an AC GPU with the rotor stationary or spinning, visually inspecting the T/R blades for burn marks, detached leading edge protection, or cracks at the skin/leading edge protection junction. If at least one T/R blade is damaged, the ASB specifies replacing all of the T/R blades. AD Requirements This AD requires, before further flight, inspecting each T/R blade for a burn mark, any disbonding of the leading edge protection, and a crack at the junction of the skin and the leading edge protection. If there is a burn mark, any disbonding of the leading edge protection, or a crack at the junction of the skin and the leading edge protection on a T/R blade, this AD requires replacing all of the T/R blades with airworthy T/R blades. This AD also requires deactivating the rotor de- icing system, revising the RFM to state that the rotor de-icing system is deactivated and that flight into known icing is prohibited, and installing a placard stating that the rotor de-icing system is deactivated. Differences Between This AD and the EASA AD The EASA AD allows operation of the rotor de-icing system with a recurring inspection of the T/R blades. This AD requires an initial inspection and prohibits operation of the rotor de-icing system by deactivating the rotor de-icing system, revising the RFM to state the rotor de-icing system is deactivated and flight into known icing is prohibited, and installing a placard stating that the rotor de-icing system is deactivated. Interim Action We consider this AD to be an interim action. Once a modification to the rotor de-icing system design is evaluated, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this AD affects 19 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD at an average labor rate of $85 per work-hour. It takes about 1 work-hour to inspect the T/R blades for a cost of $85 per helicopter and $1,615 for the U.S. [[Page 60032]] fleet. It takes about 2 work-hours to deactivate the rotor de-icing system for a cost of $170 per helicopter and $3,230 for the U.S. fleet. It takes about 0.5 work-hour to revise the RFM for a cost of $43 per helicopter and $817 for the U.S. fleet. It takes about 0.5 work-hour and a negligible parts cost to install a placard for a cost of $43 per helicopter and $817 for the U.S. fleet. Replacing a set of T/R blades takes about 3 work-hours for a labor cost of $255 per helicopter. Parts for 4-blade T/R set cost $167,644 for a total replacement cost of $167,899 per helicopter. Parts for a 5-blade T/R set cost $209,555 for a total replacement cost of $209,810 per helicopter. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we found and continue to find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the previously described unsafe condition can adversely affect the controllability of the helicopter and the initial required action must be accomplished before further flight. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment before issuing this AD were impracticable and contrary to public interest and good cause existed to make the AD effective immediately by Emergency AD 2015-18- 51, issued on September 11, 2015, to all known U.S. owners and operators of these helicopters. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. 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 We determined that 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, 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, 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): 2015-18-51 Airbus Helicopters: Amendment 39-18284; Docket No. FAA- 2015-3877; Directorate Identifier 2015-SW-039-AD. (a) Applicability This AD applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters with tail rotor (T/R) de-icing installation unit part number (P/N) 204ZP01Y01 and T/R blade P/N 332A12-0055-XX (where XX is any dash number) installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as uncontrolled and un- annunciated power supply to the T/R de-icing system, which could overheat the T/R blades. This condition could result in structural damage to the T/R blades and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective October 20, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015-18-51, issued on September 11, 2015, which contains the requirements of this AD. (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 Before further flight: (1) Inspect each T/R blade for a burn mark, any disbonding of the leading edge protection, and a crack at the junction of the skin and the leading edge protection. Examples of a burn mark, disbonding, and a crack are shown in the photos under paragraph 3.B.2., Accomplishment Instructions, of Airbus Helicopters Alert Service Bulletin No. AS332-05.01.02, Revision 0, dated July 22, 2015. If there is a burn mark, any disbonding of the leading edge protection, or a crack at the junction of the skin and the leading edge protection on a T/R blade, replace all of the T/R blades with airworthy T/R blades. (2) Deactivate the rotor de-icing system. (3) Revise Section 2, Limitations, of the Protective Equipment for Flight in Icing Conditions supplement to the rotorcraft flight manual by inserting the following: ROTOR DE-ICING SYSTEM IS DEACTIVATED. FLIGHT INTO KNOWN ICING IS PROHIBITED. (4) Install a placard with 6 millimeter red letters on a white background next to the rotors de-icing control panel that states the following: ROTOR DE-ICING SYSTEM IS DEACTIVATED. (f) Special Flight Permits Special flight permits will be permitted for flights to a location where the required inspection can be performed provided the flight does not exceed 5 hours time-in-service. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, 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 [[Page 60033]] 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. (h) Additional Information (1) Airbus Helicopters Alert Service Bulletin No. AS332- 05.01.02, Revision 0, dated July 22, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 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 Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015-0153-E, dated July 24, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2015-3877. (i) Subject Joint Aircraft Service Component (JASC) Code: 3060, Rotor De-Ice System. Issued in Fort Worth, Texas, on September 28, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-25217 Filed 10-2-15; 8:45 am] BILLING CODE 4910-13-P
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The Special Conditions the airplane is protected by the flight- DEPARTMENT OF TRANSPORTATION
■ Accordingly, pursuant to the authority control laws from getting into non-
symmetric upset conditions. The upset Federal Aviation Administration
delegated to me by the Administrator,
the following special conditions are maneuvers described in Advisory
Circular 25–7C, ‘‘Flight Test Guide for 14 CFR Part 39
issued as part of the type certification
basis for Gulfstream Model GVII–G500 Certification of Transport Category
airplanes. Airplanes,’’ section 8, paragraph 32, [Docket No. FAA–2015–3877; Directorate
1. In lieu of compliance with sub-paragraphs c(3)(a), (b), and (c), may Identifier 2015–SW–039–AD; Amendment
§ 25.335(b)(1), if the flight-control be used to comply with this 39–18284; AD 2015–18–51]
system includes functions that act requirement.
automatically to initiate recovery before RIN 2120–AA64
3. The probability of any failure of the
the end of the 20-second period high-speed protection system, which
specified in § 25.335(b)(1), VD/MD must Airworthiness Directives; Airbus
would result in an airspeed exceeding Helicopters
be determined from the greater of the
those determined by Special Conditions
speeds resulting from conditions (a) and AGENCY: Federal Aviation
1 and 2, must be less than 10¥5 per
(b) of these special conditions. The Administration (FAA), Department of
speed increase occurring in these flight hour.
Transportation (DOT).
maneuvers may be calculated if reliable 4. Failures of the system must be
ACTION: Final rule; request for
or conservative aerodynamic data are annunciated to the pilots. Flight manual
instructions must be provided that comments.
used.
(a) From an initial condition of reduce the maximum operating speeds, SUMMARY: We are publishing a new
stabilized flight at VC/MC, the airplane VMO/MMO. With the system failed, the airworthiness directive (AD) for Airbus
is upset so as to take up a new flight operating speed must be reduced to a Helicopters Model AS332C, AS332C1,
path 7.5 degrees below the initial path. value that maintains a speed margin AS332L, and AS332L1 helicopters,
Control application, up to full authority, between VMO/MMO and VD/MD, and that which was sent previously to all known
is made to try to maintain this new is consistent with showing compliance U.S. owners and operators of these
flight path. Twenty seconds after with § 25.335(b) without the benefit of helicopters. This AD requires inspecting
initiating the upset, manual recovery is the high-speed protection system. certain tail rotor (T/R) blades, replacing
made at a load factor of 1.5g (0.5 the set of T/R blades if there is damage,
acceleration increment), or such greater 5. The applicant may request that the
Master Minimum Equipment List relief deactivating the rotor de-icing system,
load factor that is automatically applied revising the rotorcraft flight manual
by the system with the pilot’s pitch for the high-speed protection system be
considered by the FAA Flight (RFM), and installing a placard. This AD
control neutral. Power, as specified in is prompted by a report of a T/R de-
§ 25.175(b)(1)(iv), is assumed until Operations Evaluation Board, provided
icing system power supply box stuck in
recovery is initiated, at which time that the flight manual instructions
a ‘‘closed’’ position providing an
power reduction, and the use of pilot- indicate reduced maximum operating uncontrolled and un-annunciated power
controlled drag devices, may be used. speeds as described in Special supply to the system. These actions are
(b) From a speed below VC/MC, with Condition 4. In addition, the flightdeck intended to detect and prevent
power to maintain stabilized level flight display of the reduced operating speeds, structural damage to the T/R blades
at this speed, the airplane is upset so as as well as the overspeed warning for caused by overheating, and subsequent
to accelerate through VC/MC at a flight exceeding those speeds, must be loss of control of the helicopter.
path 15 degrees below the initial path equivalent to that of the normal airplane DATES: This AD becomes effective
(or at the steepest nose-down attitude with the high-speed protection system
that the system will permit with full October 20, 2015 to all persons except
operative. Also, the applicant must those persons to whom it was made
control authority if less than 15 show that no additional hazards are
degrees). The pilot’s controls may be in immediately effective by Emergency AD
introduced with the high-speed 2015–18–51, issued on September 11,
the neutral position after reaching VC/ protection system inoperative.
MC and before recovery is initiated. 2015, which contains the requirements
Recovery may be initiated 3 seconds Issued in Renton, Washington, September of this AD.
after operation of the high-speed 25, 2015. We must receive comments on this
warning system by application of a load Michael Kaszycki, AD by December 4, 2015.
of 1.5g (0.5 acceleration increment), or Acting Manager, Transport Airplane ADDRESSES: You may send comments by
such greater load factor that is Directorate, Aircraft Certification Service. any of the following methods:
automatically applied by the system [FR Doc. 2015–25275 Filed 10–2–15; 8:45 am] • Federal eRulemaking Docket: Go to
with the pilot’s pitch control neutral. BILLING CODE 4910–13–P
http://www.regulations.gov. Follow the
Power may be reduced simultaneously. online instructions for sending your
All other means of decelerating the comments electronically.
airplane, the use of which is authorized • Fax: 202–493–2251.
up to the highest speed reached in the • Mail: Send comments to the U.S.
maneuver, may be used. The interval Department of Transportation, Docket
between successive pilot actions must Operations, M–30, West Building
mstockstill on DSK4VPTVN1PROD with RULES
not be less than 1 second. Ground Floor, Room W12–140, 1200
2. The applicant must also New Jersey Avenue SE., Washington,
demonstrate that the speed margin, DC 20590–0001.
established as above, will not be • Hand Delivery: Deliver to the
exceeded in inadvertent or gust-induced ‘‘Mail’’ address between 9 a.m. and
upsets resulting in initiation of the dive 5 p.m., Monday through Friday, except
from non-symmetric attitudes, unless Federal holidays.
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fleet. It takes about 2 work-hours to the Administrator finds necessary for 0055–XX (where XX is any dash number)
deactivate the rotor de-icing system for safety in air commerce. This regulation installed, certificated in any category.
a cost of $170 per helicopter and $3,230 is within the scope of that authority (b) Unsafe Condition
for the U.S. fleet. It takes about 0.5 because it addresses an unsafe condition This AD defines the unsafe condition as
work-hour to revise the RFM for a cost that is likely to exist or develop on uncontrolled and un-annunciated power
of $43 per helicopter and $817 for the products identified in this rulemaking supply to the T/R de-icing system, which
U.S. fleet. It takes about 0.5 work-hour action. could overheat the T/R blades. This
and a negligible parts cost to install a condition could result in structural damage
placard for a cost of $43 per helicopter Regulatory Findings to the T/R blades and subsequent loss of
and $817 for the U.S. fleet. Replacing a We determined that this AD will not control of the helicopter.
set of T/R blades takes about 3 work- have federalism implications under (c) Effective Date
hours for a labor cost of $255 per Executive Order 13132. This AD will
This AD becomes effective October 20,
helicopter. Parts for 4-blade T/R set cost not have a substantial direct effect on 2015 to all persons except those persons to
$167,644 for a total replacement cost of the States, on the relationship between whom it was made immediately effective by
$167,899 per helicopter. Parts for a 5- the national Government and the States, Emergency AD 2015–18–51, issued on
blade T/R set cost $209,555 for a total or on the distribution of power and September 11, 2015, which contains the
replacement cost of $209,810 per responsibilities among the various requirements of this AD.
helicopter. levels of government. (d) Compliance
For the reasons discussed, I certify
FAA’s Justification and Determination You are responsible for performing each
that this AD: action required by this AD within the
of the Effective Date 1. Is not a ‘‘significant regulatory specified compliance time unless it has
Providing an opportunity for public action’’ under Executive Order 12866; already been accomplished prior to that time.
comments prior to adopting these AD 2. Is not a ‘‘significant rule’’ under
requirements would delay DOT Regulatory Policies and Procedures (e) Required Actions
implementing the safety actions needed (44 FR 11034, February 26, 1979); Before further flight:
to correct this known unsafe condition. 3. Will not affect intrastate aviation in (1) Inspect each T/R blade for a burn mark,
Therefore, we found and continue to Alaska to the extent that it justifies any disbonding of the leading edge
find that the risk to the flying public making a regulatory distinction; and protection, and a crack at the junction of the
skin and the leading edge protection.
justifies waiving notice and comment 4. Will not have a significant
Examples of a burn mark, disbonding, and a
prior to the adoption of this rule economic impact, positive or negative, crack are shown in the photos under
because the previously described unsafe on a substantial number of small entities paragraph 3.B.2., Accomplishment
condition can adversely affect the under the criteria of the Regulatory Instructions, of Airbus Helicopters Alert
controllability of the helicopter and the Flexibility Act. Service Bulletin No. AS332–05.01.02,
initial required action must be We prepared an economic evaluation Revision 0, dated July 22, 2015. If there is a
accomplished before further flight. of the estimated costs to comply with burn mark, any disbonding of the leading
Since it was found that immediate this AD and placed it in the AD docket. edge protection, or a crack at the junction of
corrective action was required, notice the skin and the leading edge protection on
List of Subjects in 14 CFR Part 39 a T/R blade, replace all of the T/R blades
and opportunity for prior public with airworthy T/R blades.
comment before issuing this AD were Air transportation, Aircraft, Aviation
(2) Deactivate the rotor de-icing system.
impracticable and contrary to public safety, Incorporation by reference, (3) Revise Section 2, Limitations, of the
interest and good cause existed to make Safety. Protective Equipment for Flight in Icing
the AD effective immediately by Adoption of the Amendment Conditions supplement to the rotorcraft flight
Emergency AD 2015–18–51, issued on manual by inserting the following: ROTOR
September 11, 2015, to all known U.S. Accordingly, under the authority DE–ICING SYSTEM IS DEACTIVATED.
owners and operators of these delegated to me by the Administrator, FLIGHT INTO KNOWN ICING IS
the FAA amends 14 CFR part 39 as PROHIBITED.
helicopters. These conditions still exist (4) Install a placard with 6 millimeter red
and the AD is hereby published in the follows:
letters on a white background next to the
Federal Register as an amendment to rotors de-icing control panel that states the
PART 39—AIRWORTHINESS
section 39.13 of the Federal Aviation following: ROTOR DE–ICING SYSTEM IS
DIRECTIVES
Regulations (14 CFR 39.13) to make it DEACTIVATED.
effective to all persons. ■ 1. The authority citation for part 39 (f) Special Flight Permits
Authority for This Rulemaking continues to read as follows: Special flight permits will be permitted for
Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701. flights to a location where the required
specifies the FAA’s authority to issue inspection can be performed provided the
§ 39.13 [Amended] flight does not exceed 5 hours time-in-
rules on aviation safety. Subtitle I, service.
section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding
the FAA Administrator. ‘‘Subtitle VII: the following new airworthiness (g) Alternative Methods of Compliance
Aviation Programs,’’ describes in more directive (AD): (AMOCs)
detail the scope of the Agency’s 2015–18–51 Airbus Helicopters: (1) The Manager, Safety Management
authority. Amendment 39–18284; Docket No. Group, FAA, may approve AMOCs for this
We are issuing this rulemaking under FAA–2015–3877; Directorate Identifier AD. Send your proposal to: George Schwab,
mstockstill on DSK4VPTVN1PROD with RULES
the authority described in ‘‘Subtitle VII, 2015–SW–039–AD. Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Part A, Subpart III, Section 44701: (a) Applicability Hillwood Pkwy, Fort Worth, TX 76177;
General requirements.’’ Under that This AD applies to Airbus Helicopters telephone (817) 222–5110; email 9-ASW-
section, Congress charges the FAA with Model AS332C, AS332C1, AS332L, and FTW-AMOC-Requests@faa.gov.
promoting safe flight of civil aircraft in AS332L1 helicopters with tail rotor (T/R) de- (2) For operations conducted under a 14
air commerce by prescribing regulations icing installation unit part number (P/N) CFR part 119 operating certificate or under
for practices, methods, and procedures 204ZP01Y01 and T/R blade P/N 332A12– 14 CFR part 91, subpart K, we suggest that
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![Federal Register / Vol. 80, No. 192 / Monday, October 5, 2015 / Rules and Regulations 60033
you notify your principal inspector, or Background additional clarification regarding the
lacking a principal inspector, the manager of applicability of the standards to certain
the local flight standards district office or The Federal Aviation Administration
(FAA) Flight Services is revising FAA operations, including some tree
certificate holding district office, before
operating any aircraft complying with this Order JO 7930.2, Notices to Airmen trimming work that is performed near
AD through an AMOC. (NOTAM), which is scheduled to (but that is not on or directly associated
become effective no later than December with) electric power generation,
(h) Additional Information transmission, and distribution
15, 2015.
(1) Airbus Helicopters Alert Service The following paragraphs will be installations. This document also
Bulletin No. AS332–05.01.02, Revision 0, corrects minor errors in two minimum
dated July 22, 2015, which is not
incorporated into the next revision of
FAA Order JO 7930.2. approach distance tables in the general
incorporated by reference, contains
additional information about the subject of Paragraph 4–2–1a–14, Start of industry and construction standards for
this AD. For service information identified in Activity/End of Validity, is ‘‘a 10-digit electric power generation, transmission
this AD, contact Airbus Helicopters, 2701 N. date-time group (YYMMDDHHMM) and distribution work.
Forum Drive, Grand Prairie, TX 75052; used to indicate the time at which the
telephone (972) 641–0000 or (800) 232–0323;
DATES: These correcting amendments
NOT AM comes into force (the date/ are effective on October 5, 2015.
fax (972) 641–3775; or at http:// time a condition will exist or begin) and
www.airbushelicopters.com/techpub. You the time at which the NOTAM ceases to FOR FURTHER INFORMATION CONTACT:
may review a copy of the service information
be in force and becomes invalid (the General information and press inquiries:
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., expected return to service, return to Mr. Frank Meilinger, Office of
Room 6N–321, Fort Worth, TX 76177. normal status time, or the time the Communications, Room N3647, OSHA,
(2) The subject of this AD is addressed in activity will end).’’ U.S. Department of Labor, 200
European Aviation Safety Agency (EASA) AD Paragraph 4–2–1a–14(a) further Constitution Avenue NW., Washington,
No. 2015–0153–E, dated July 24, 2015. You specifies, that if the NOTAM duration is DC 20210; telephone (202) 693–1999;
may view the EASA AD on the Internet at expected to return to service prior to the email meilingerfrancis2@dol.gov.
http://www.regulations.gov by searching for End of Validity time, express the time
and locating it in Docket No. FAA–2015– Technical information: Mr. William
by using a date- time group followed Perry, Directorate of Standards and
3877.
immediately by EST. The NOTAM Guidance, Room N3718, OSHA, U.S.
(i) Subject Originator must cancel or replace any Department of Labor, 200 Constitution
Joint Aircraft Service Component (JASC) NOTAM that includes an EST before the Avenue NW., Washington, DC 20210;
Code: 3060, Rotor De-Ice System. NOTAM reaches its End of Validity
telephone (202) 693–1950 or fax (202)
Issued in Fort Worth, Texas, on September time, as the NOTAM will now auto
693–1678; email perry.bill@dol.gov.
28, 2015. expire at the end of validity time,
Lance T. Gant, regardless of EST. SUPPLEMENTARY INFORMATION: This
Acting Directorate Manager, Rotorcraft Issued in Washington, DC, on September document revises certain language in
Directorate, Aircraft Certification Service. 23, 2015. OSHA’s standards to reflect the
[FR Doc. 2015–25217 Filed 10–2–15; 8:45 am] Ernie Bilotto, Agency’s intent about the scope of two
BILLING CODE 4910–13–P Manager, U.S. NOTAMs. general industry standards. First, this
[FR Doc. 2015–25192 Filed 10–2–15; 8:45 am]
document revises language that
mistakenly could be read as suggesting
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION that the general industry electric power
generation, transmission, and
Federal Aviation Administration distribution standard covers certain
DEPARTMENT OF LABOR tree-trimming work that is performed
14 CFR Chapter I Occupational Safety and Health near, but that is not on or directly
Administration associated with, electric power
Change in EST Usage in Notice to generation, transmission, and
Airmen (NOTAM) distribution installations. This was
29 CFR Parts 1910, 1926
AGENCY: Federal Aviation never OSHA’s intent; rather, OSHA
Administration (FAA), DOT. [Docket Nos. S–016 (OSHA–S016–2006– intended that the general industry
0646), OSHA–S215–2006–0063] electrical safety-related work practices
ACTION: Policy change.
RIN 1218–AA32, 1218–AB67 standard cover such work. Similarly,
SUMMARY: This document provides OSHA is correcting language in its
clarity and guidance regarding the use Electrical Safety-Related Work general industry electrical safety-related
of the contraction ‘‘EST’’, which stands Practices; Electric Power Generation, work practices standard to make clear
for ‘‘Estimated’’, when appended to the Transmission, and Distribution; that the standard covers other work
end of validity time in a NOTAM. The Electrical Protective Equipment; performed by qualified persons that is
FAA is taking this action to align Corrections near, but not on or directly associated
NOTAM policy with International Civil with, both electric power generation,
Aviation Organization (ICAO) standards AGENCY: Occupational Safety and Health
transmission, and distribution
and recommended practices. Administration (OSHA), Labor.
installations and certain other types of
ACTION: Correcting amendments.
mstockstill on DSK4VPTVN1PROD with RULES
DATES: Effective date: December 15, installations.
2015. This notice also corrects minor errors
SUMMARY: This document corrects the
FOR FURTHER INFORMATION CONTACT: Gary electrical safety-related work practices in two minimum approach distance
Bobik (202–267–6524; gary.ctr.bobik@ standard for general industry and the tables in the general industry and
faa.gov) or Lynette Jamison (540–422– electric power generation, transmission, construction standards for electric
4761; lynette.m.jamison@faa.gov) and distribution standards for general power generation, transmission and
SUPPLEMENTARY INFORMATION: industry and construction to provide distribution work.
VerDate Sep<11>2014 16:55 Oct 02, 2015 Jkt 238001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\05OCR1.SGM 05OCR1](https://thefederalregister.org/doc/80_FR_60222/page/4.svg)
Document Created: 2015-12-15 08:52:40
Document Modified: 2015-12-15 08:52:40
| 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 becomes effective October 20, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015-18-51, issued on September 11, 2015, which contains the requirements of this AD. | |
| Contact | George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 60030 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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