Special Conditions: JAMCO America, Inc., Boeing Model 777-300ER, Dynamic Test Requirements for Single-Occupant Oblique (Side-Facing) Seats With Inflatable Restraints, 43471-43472 [2016-15784]

Download as PDF sradovich on DSK3GDR082PROD with RULES Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations i. normal operations; ii. any probable failure conditions of charging or discharging or battery monitoring system; or iii. any failure of the charging or battery monitoring system not shown to be extremely remote. (2) The rechargeable lithium battery installation must be designed to preclude explosion or fire in the event of (e)(1)(ii) and (e)(1)(iii) failures. (3) Design of the rechargeable lithium batteries must preclude the occurrence of self-sustaining, uncontrolled increases in temperature or pressure. (4) No explosive or toxic gasses emitted by any rechargeable lithium battery in normal operation or as the result of any failure of the battery charging system, monitoring system, or battery installation that is not shown to be extremely remote, may accumulate in hazardous quantities within the airplane. (5) Installations of rechargeable lithium batteries must meet the requirements of § 23.863(a) through (d) at amendment 23–34. (6) No corrosive fluids or gases that may escape from any rechargeable lithium battery may damage surrounding structure or any adjacent systems, equipment, electrical wiring, or the airplane in such a way as to cause a major or more severe failure condition, in accordance with § 23.1309(c) at amendment 23–62 and applicable regulatory guidance. (7) Each rechargeable lithium battery installation must have provisions to prevent any hazardous effect on structure or essential systems that may be caused by the maximum amount of heat the battery can generate during a short circuit of the battery or of its individual cells. (8) Rechargeable lithium battery installations must have— i. a system to automatically control the charging rate of the battery to prevent battery overheating and overcharging; ii. a battery temperature sensing and over-temperature warning system with a means of automatically disconnecting the battery from its charging source in the event of an over-temperature condition; and iii. a battery failure sensing and warning system with a means of automatically disconnecting the battery from its charging source in the event of battery failure. (b) Any rechargeable lithium battery installation functionally required for safe operation of the airplane must incorporate a monitoring and warning feature that will provide an indication to the appropriate flight crewmembers VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 whenever the State of Charge (SOC) of the batteries has fallen below levels considered acceptable for dispatch of the airplane. (c) The Instructions for Continued Airworthiness required by § 23.1529 at amendment 23–26 must contain maintenance requirements to assure that the battery has been sufficiently charged at appropriate intervals specified by the battery manufacturer and the equipment manufacturer that contain the rechargeable lithium battery or rechargeable lithium battery system. This is required to ensure that lithium rechargeable batteries and lithium rechargeable battery systems will not degrade below specified ampere-hour levels sufficient to power the aircraft system. The Instructions for Continued Airworthiness must also contain procedures for the maintenance of replacement batteries in spares storage to prevent the installation of batteries that have degraded charge retention ability or other damage due to prolonged storage at a low state of charge. Replacement batteries must be of the same manufacturer and part number as approved by the FAA. Issued in Kansas City, Missouri, on June 23, 2016. William Schinstock, Acting Manager, Small Airplane Directorate Aircraft Certification Service. [FR Doc. 2016–15765 Filed 7–1–16; 8:45 am] BILLING CODE 4910–13–P 43471 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. DATES: 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 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 SingleOccupant Oblique (Side-Facing) Seats With Inflatable Restraints Federal Aviation Administration (FAA), DOT. ACTION: Final special condition; request for comments; corrections. AGENCY: 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. SUMMARY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 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 § 25.562: 1. Head Injury Criteria (HIC) Compliance with § 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 E:\FR\FM\05JYR1.SGM 05JYR1 43472 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 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. sradovich on DSK3GDR082PROD with RULES 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 neckinjury 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. VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 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 mostcritical 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8134; Directorate Identifier 2014–NM–256–AD; Amendment 39–18572; AD 2016–13–08] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Airbus Model A300 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). This AD was prompted by a report of cracking of the lower tension bolt area at the rib one junction (both sides) of the lower wing. This AD requires repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the frame (FR) 40 lower wing location, and corrective actions if necessary. We are issuing this AD to detect and correct crack initiation of the fittings of the FR40 lower wing locations, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective August 9, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 9, 2016. ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; Internet https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2015–8134. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8134; 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 Operations office (telephone 800–647–5527) is in the ADDRESSES section. Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: E:\FR\FM\05JYR1.SGM 05JYR1

Agencies

[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)]
[Rules and Regulations]
[Pages 43471-43472]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.