81 FR 43471 - Special Conditions: JAMCO America, Inc., Boeing Model 777-300ER, Dynamic Test Requirements for Single-Occupant Oblique (Side-Facing) Seats With Inflatable Restraints
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 128 (July 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 128 (July 5, 2016)
| Page Range | 43471-43472 | |
| FR Document | 2016-15784 |
[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)] [Rules and Regulations] [Pages 43471-43472] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15784] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA-2015-8298; Special Conditions No. 25-611-SC] Special Conditions: JAMCO America, Inc., Boeing Model 777-300ER, Dynamic Test Requirements for Single-Occupant Oblique (Side-Facing) Seats With Inflatable Restraints AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special condition; request for comments; corrections. ----------------------------------------------------------------------- SUMMARY: This document corrects omissions in docket no. FAA-2015-8298, special conditions no. 25-611-SC, which was published in the Federal Register on March 16, 2016 (81 FR 13969). The special conditions in the published document are incomplete. This correction replaces the entire special conditions section from that which appeared in the original Federal Register publication. DATES: This action is effective on JAMCO America, Inc., on July 5, 2016. We must receive your comments August 19, 2016. FOR FURTHER INFORMATION CONTACT: John Shelden, FAA, Airframe and Cabin Safety Branch, ANM-115,Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057- 3356; telephone (425) 227-2785; facsimile (425) 227-1320. SUPPLEMENTARY INFORMATION: On March 16, 2016, the Federal Register published a document designated as ``Docket No. FAA-2015-8298; Special Conditions No. 25-611-SC,'' (81 FR 13969). That document issued special conditions pertaining to dynamic test requirements for single-occupant oblique (side-facing) seats with inflatable restraints on Boeing Model 777-300ER airplanes. As published, the special conditions are incomplete. The applicant was aware of the complete set of conditions at the time of the original, incomplete publication. Correction The following special conditions replace the entire special conditions section of the final special conditions document [FR Doc. 2016-05995 Filed 3-15-16; 8:45 a.m.], published on March 16, 2016 (81 FR 13969). The introductory language was previously published and is not changed. The Special Conditions 0 Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Boeing Model 777-300ER airplanes modified by JAMCO. Oblique (Side-Facing) Seats Special Conditions In addition to the requirements of Sec. 25.562: 1. Head Injury Criteria (HIC) Compliance with Sec. 25.562(c)(5) is required, except that, if the anthropomorphic test device (ATD) has no apparent contact with the seat and related structure but has contact with an airbag, a HIC unlimited score in excess of 1000 is acceptable, provided the HIC15 score (calculated in accordance with 49 CFR 571.208) for that contact is less than 700. 2. Body-to-Wall/Furnishing Contact If a seat is installed aft of structure (e.g. interior wall or furnishings) that does not provide a homogenous contact surface for the expected range of occupants and yaw angles, then [[Page 43472]] additional analysis and tests may be required to demonstrate that the injury criteria are met for the area that an occupant could contact. For example, if different yaw angles could result in different airbag device performance, then additional analysis or separate tests may be necessary to evaluate performance. 3. Neck Injury Criteria a. The seating system must protect the occupant from experiencing serious neck injury. The assessment of neck injury must be conducted with the airbag device activated, unless there is reason to also consider that the neck-injury potential would be higher for impacts below the airbag-device deployment threshold. b. The Nij , calculated in accordance with 49 CFR 571.208, must be below 1.0, where Nij =Fz / Fzc + My /Myc , and Nij critical values are: i. Fzc = 1530 lb for tension ii. Fzc = 1385 lb for compression iii. Myc = 229 lb-ft in flexion iv. Myc = 100 lb-ft in extension c. In addition, peak upper neck Fz must be below 937 lb in tension and 899 lb in compression. d. Rotation of the head about its vertical axis relative to the torso is limited to 105 degrees in either direction from forward- facing. e. The neck must not impact any surface that would produce concentrated loading on the neck. 4. Spine and Torso Injury Criteria a. The lumbar spine tension (Fz ) cannot exceed 1200 lb. b. Significant concentrated loading on the occupant's spine, in the area between the pelvis and shoulders during impact, including rebound, is not acceptable. During this type of contact, the interval for any rearward (X-axis direction) acceleration exceeding 20g must be less than 3 milliseconds as measured by the thoracic instrumentation specified in 49 CFR part 572, subpart E, filtered in accordance with SAE recommended practice J211/1, ``Instrumentation for Impact Test-- Part 1--Electronic Instrumentation.'' c. The occupant must not interact with the armrest or other seat components in any manner significantly different than would be expected for a forward-facing seat installation. 5. Pelvis Criteria Any part of the load-bearing portion of the bottom of the ATD pelvis must not translate beyond the edges of the seat bottom seat- cushion supporting structure. 6. Femur Criteria Axial rotation of the upper leg (about the Z-axis of the femur, per SAE J211/1) must be limited to 35 degrees in the strike direction from the normal seating position. Evaluation during rebound need not be considered. 7. ATD and Test Conditions Longitudinal tests conducted to measure the injury criteria above must be performed with the FAA Hybrid III ATD, as described in SAE 1999-01-1609, ``A Lumbar Spine Modification to the Hybrid III ATD For Aircraft Seat Tests.'' The tests must be conducted with an undeformed floor, at the most-critical yaw cases for injury, and with all lateral structural supports (e.g. armrests or walls) installed. Inflatable Lapbelt Special Conditions The inflatable lapbelts must meet special conditions no. 25-187A- SC, ``Boeing Model 777 Series Airplanes; Seats with Inflatable Lapbelts.'' 1. Because this type of protection system may or may not activate during various crash conditions, the applicant must demonstrate that the injury criteria listed in these special conditions are not exceeded in an event which is slightly below the activation level of the airbag system. 2. Additionally, as indicated in special conditions no. 25-187A-SC, inflatable lapbelts must be shown to not affect emergency-egress capabilities in the main aisle, cross-aisle, and passageway. Issued in Renton, Washington, on June 17, 2016. Michael Kaszycki, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-15784 Filed 7-1-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43471
i. normal operations; whenever the State of Charge (SOC) of DATES: This action is effective on
ii. any probable failure conditions of the batteries has fallen below levels JAMCO America, Inc., on July 5, 2016.
charging or discharging or battery considered acceptable for dispatch of We must receive your comments August
monitoring system; or the airplane. 19, 2016.
iii. any failure of the charging or (c) The Instructions for Continued FOR FURTHER INFORMATION CONTACT: John
battery monitoring system not shown to Airworthiness required by § 23.1529 at Shelden, FAA, Airframe and Cabin
be extremely remote. amendment 23–26 must contain Safety Branch, ANM–115,Transport
(2) The rechargeable lithium battery maintenance requirements to assure that Airplane Directorate, Aircraft
installation must be designed to the battery has been sufficiently charged Certification Service, 1601 Lind Avenue
preclude explosion or fire in the event at appropriate intervals specified by the SW., Renton, Washington 98057–3356;
of (e)(1)(ii) and (e)(1)(iii) failures. battery manufacturer and the equipment telephone (425) 227–2785; facsimile
(3) Design of the rechargeable lithium manufacturer that contain the (425) 227–1320.
batteries must preclude the occurrence rechargeable lithium battery or SUPPLEMENTARY INFORMATION: On March
of self-sustaining, uncontrolled rechargeable lithium battery system. 16, 2016, the Federal Register published
increases in temperature or pressure. This is required to ensure that lithium a document designated as ‘‘Docket No.
(4) No explosive or toxic gasses rechargeable batteries and lithium FAA–2015–8298; Special Conditions
emitted by any rechargeable lithium rechargeable battery systems will not No. 25–611–SC,’’ (81 FR 13969). That
battery in normal operation or as the degrade below specified ampere-hour document issued special conditions
result of any failure of the battery levels sufficient to power the aircraft pertaining to dynamic test requirements
charging system, monitoring system, or system. The Instructions for Continued for single-occupant oblique (side-facing)
battery installation that is not shown to Airworthiness must also contain seats with inflatable restraints on Boeing
be extremely remote, may accumulate in procedures for the maintenance of Model 777–300ER airplanes. As
hazardous quantities within the replacement batteries in spares storage published, the special conditions are
airplane. to prevent the installation of batteries incomplete. The applicant was aware of
(5) Installations of rechargeable that have degraded charge retention the complete set of conditions at the
lithium batteries must meet the ability or other damage due to time of the original, incomplete
requirements of § 23.863(a) through (d) prolonged storage at a low state of publication.
at amendment 23–34. charge. Replacement batteries must be
(6) No corrosive fluids or gases that of the same manufacturer and part Correction
may escape from any rechargeable number as approved by the FAA. The following special conditions
lithium battery may damage replace the entire special conditions
Issued in Kansas City, Missouri, on June
surrounding structure or any adjacent section of the final special conditions
23, 2016.
systems, equipment, electrical wiring, or document [FR Doc. 2016–05995 Filed
William Schinstock,
the airplane in such a way as to cause 3–15–16; 8:45 a.m.], published on
a major or more severe failure condition, Acting Manager, Small Airplane Directorate
Aircraft Certification Service. March 16, 2016 (81 FR 13969). The
in accordance with § 23.1309(c) at introductory language was previously
[FR Doc. 2016–15765 Filed 7–1–16; 8:45 am]
amendment 23–62 and applicable published and is not changed.
regulatory guidance. BILLING CODE 4910–13–P
(7) Each rechargeable lithium battery The Special Conditions
installation must have provisions to ■ Accordingly, pursuant to the authority
prevent any hazardous effect on DEPARTMENT OF TRANSPORTATION
delegated to me by the Administrator,
structure or essential systems that may Federal Aviation Administration the following special conditions are
be caused by the maximum amount of issued as part of the type certification
heat the battery can generate during a 14 CFR Part 25 basis for Boeing Model 777–300ER
short circuit of the battery or of its airplanes modified by JAMCO.
individual cells. [Docket No. FAA–2015–8298; Special
(8) Rechargeable lithium battery Conditions No. 25–611–SC] Oblique (Side-Facing) Seats Special
installations must have— Conditions
i. a system to automatically control Special Conditions: JAMCO America,
Inc., Boeing Model 777–300ER, In addition to the requirements of
the charging rate of the battery to § 25.562:
prevent battery overheating and Dynamic Test Requirements for Single-
overcharging; Occupant Oblique (Side-Facing) Seats 1. Head Injury Criteria (HIC)
ii. a battery temperature sensing and With Inflatable Restraints
Compliance with § 25.562(c)(5) is
over-temperature warning system with a AGENCY: Federal Aviation required, except that, if the
means of automatically disconnecting Administration (FAA), DOT. anthropomorphic test device (ATD) has
the battery from its charging source in ACTION: Final special condition; request no apparent contact with the seat and
the event of an over-temperature for comments; corrections. related structure but has contact with an
condition; and airbag, a HIC unlimited score in excess
iii. a battery failure sensing and SUMMARY: This document corrects of 1000 is acceptable, provided the
warning system with a means of omissions in docket no. FAA–2015– HIC15 score (calculated in accordance
automatically disconnecting the battery 8298, special conditions no. 25–611–SC, with 49 CFR 571.208) for that contact is
from its charging source in the event of which was published in the Federal less than 700.
sradovich on DSK3GDR082PROD with RULES
battery failure. Register on March 16, 2016 (81 FR
(b) Any rechargeable lithium battery 13969). The special conditions in the 2. Body-to-Wall/Furnishing Contact
installation functionally required for published document are incomplete. If a seat is installed aft of structure
safe operation of the airplane must This correction replaces the entire (e.g. interior wall or furnishings) that
incorporate a monitoring and warning special conditions section from that does not provide a homogenous contact
feature that will provide an indication which appeared in the original Federal surface for the expected range of
to the appropriate flight crewmembers Register publication. occupants and yaw angles, then
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![43472 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations
additional analysis and tests may be 6. Femur Criteria Airbus Model A300 series airplanes;
required to demonstrate that the injury Axial rotation of the upper leg (about and Model A300 B4–600, B4–600R, and
criteria are met for the area that an the Z-axis of the femur, per SAE J211/ F4–600R series airplanes, and Model
occupant could contact. For example, if 1) must be limited to 35 degrees in the A300 C4–605R Variant F airplanes
different yaw angles could result in strike direction from the normal seating (collectively called Model A300–600
different airbag device performance, position. Evaluation during rebound series airplanes). This AD was prompted
then additional analysis or separate tests need not be considered. by a report of cracking of the lower
may be necessary to evaluate tension bolt area at the rib one junction
performance. 7. ATD and Test Conditions (both sides) of the lower wing. This AD
Longitudinal tests conducted to requires repetitive inspections for
3. Neck Injury Criteria
measure the injury criteria above must cracking of the fasteners and of the
a. The seating system must protect the be performed with the FAA Hybrid III fitting around the fastener holes at the
occupant from experiencing serious ATD, as described in SAE 1999–01– frame (FR) 40 lower wing location, and
neck injury. The assessment of neck 1609, ‘‘A Lumbar Spine Modification to corrective actions if necessary. We are
injury must be conducted with the the Hybrid III ATD For Aircraft Seat issuing this AD to detect and correct
airbag device activated, unless there is Tests.’’ The tests must be conducted crack initiation of the fittings of the
reason to also consider that the neck- with an undeformed floor, at the most- FR40 lower wing locations, which could
injury potential would be higher for critical yaw cases for injury, and with result in reduced structural integrity of
impacts below the airbag-device all lateral structural supports (e.g. the airplane.
deployment threshold. armrests or walls) installed. DATES: This AD becomes effective
b. The Nij, calculated in accordance
Inflatable Lapbelt Special Conditions August 9, 2016.
with 49 CFR 571.208, must be below
The Director of the Federal Register
1.0, where Nij =Fz/Fzc + My/Myc, and Nij The inflatable lapbelts must meet
approved the incorporation by reference
critical values are: special conditions no. 25–187A–SC,
‘‘Boeing Model 777 Series Airplanes; of certain publications listed in this AD
i. Fzc = 1530 lb for tension as of August 9, 2016.
ii. Fzc = 1385 lb for compression Seats with Inflatable Lapbelts.’’
iii. Myc = 229 lb-ft in flexion 1. Because this type of protection ADDRESSES: For Airbus service
iv. Myc = 100 lb-ft in extension system may or may not activate during information identified in this final rule,
c. In addition, peak upper neck Fz various crash conditions, the applicant contact Airbus SAS, Airworthiness
must be below 937 lb in tension and 899 must demonstrate that the injury criteria Office—EAW, 1 Rond Point Maurice
lb in compression. listed in these special conditions are not Bellonte, 31707 Blagnac Cedex, France;
d. Rotation of the head about its exceeded in an event which is slightly telephone +33 5 61 93 36 96; fax +33 5
vertical axis relative to the torso is below the activation level of the airbag 61 93 44 51; email account.airworth-
limited to 105 degrees in either system. eas@airbus.com; Internet http://
direction from forward-facing. 2. Additionally, as indicated in www.airbus.com. You may view this
e. The neck must not impact any special conditions no. 25–187A–SC, referenced service information at the
surface that would produce inflatable lapbelts must be shown to not FAA, Transport Airplane Directorate,
concentrated loading on the neck. affect emergency-egress capabilities in 1601 Lind Avenue SW., Renton, WA.
the main aisle, cross-aisle, and For information on the availability of
4. Spine and Torso Injury Criteria passageway. this material at the FAA, call 425–227–
a. The lumbar spine tension (Fz) Issued in Renton, Washington, on June 17, 1221. It is also available on the Internet
cannot exceed 1200 lb. 2016. at http://www.regulations.gov by
b. Significant concentrated loading on Michael Kaszycki, searching for and locating Docket No.
the occupant’s spine, in the area Assistant Manager, Transport Airplane FAA–2015–8134.
between the pelvis and shoulders Directorate, Aircraft Certification Service.
during impact, including rebound, is Examining the AD Docket
[FR Doc. 2016–15784 Filed 7–1–16; 8:45 am]
not acceptable. During this type of You may examine the AD docket on
BILLING CODE 4910–13–P
contact, the interval for any rearward the Internet at http://
(X-axis direction) acceleration www.regulations.gov by searching for
exceeding 20g must be less than 3 DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2015–
milliseconds as measured by the 8134; or in person at the Docket
thoracic instrumentation specified in 49 Federal Aviation Administration Management Facility between 9 a.m.
CFR part 572, subpart E, filtered in and 5 p.m., Monday through Friday,
accordance with SAE recommended 14 CFR Part 39 except Federal holidays. The AD docket
practice J211/1, ‘‘Instrumentation for contains this AD, the regulatory
[Docket No. FAA–2015–8134; Directorate
Impact Test—Part 1—Electronic Identifier 2014–NM–256–AD; Amendment evaluation, any comments received, and
Instrumentation.’’ 39–18572; AD 2016–13–08] other information. The street address for
c. The occupant must not interact the Docket Operations office (telephone
with the armrest or other seat RIN 2120–AA64 800–647–5527) is in the ADDRESSES
components in any manner significantly section.
different than would be expected for a Airworthiness Directives; Airbus
forward-facing seat installation. Airplanes FOR FURTHER INFORMATION CONTACT: Dan
sradovich on DSK3GDR082PROD with RULES
Rodina, Aerospace Engineer,
5. Pelvis Criteria AGENCY: Federal Aviation
International Branch, ANM–116,
Administration (FAA), Department of
Any part of the load-bearing portion Transport Airplane Directorate, FAA,
Transportation (DOT).
of the bottom of the ATD pelvis must 1601 Lind Avenue SW., Renton, WA
ACTION: Final rule.
not translate beyond the edges of the 98057–3356; telephone 425–227–2125;
seat bottom seat-cushion supporting SUMMARY: We are adopting a new fax 425–227–1149.
structure. airworthiness directive (AD) for all SUPPLEMENTARY INFORMATION:
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Document Created: 2016-07-01 23:49:31
Document Modified: 2016-07-01 23:49:31
| 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 special condition; request for comments; corrections. | |
| Dates | This action is effective on JAMCO America, Inc., on July 5, 2016. We must receive your comments August 19, 2016. | |
| Contact | John Shelden, FAA, Airframe and Cabin Safety Branch, ANM-115,Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057- 3356; telephone (425) 227-2785; facsimile (425) 227-1320. | |
| FR Citation | 81 FR 43471 |
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