[Federal Register Volume 74, Number 167 (Monday, August 31, 2009)]
[Rules and Regulations]
[Pages 44730-44732]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-20742]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM406; Special Conditions No. 25-384-SC]


Special Conditions: Bombardier Inc. Model CL-600-2B19, -2C10, -
2D15 and -2D24 Airplanes; Passenger Seats With Non-Traditional, Large, 
Non-Metallic Panels

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for Bombardier Inc. model 
CL-600-2B19, -2C10, -2D15 and -2D24 airplanes. These airplanes will 
have a novel or unusual design feature(s) associated with seats that 
include non-traditional, large, non-metallic panels that would affect 
survivability during a post-crash fire event. The applicable 
airworthiness regulations do not contain adequate or appropriate safety 
standards for this design feature. These special conditions contain the 
additional safety standards that the Administrator considers necessary 
to establish a level of safety equivalent to that established by the 
existing airworthiness standards.

DATES: Effective Date: August 12, 2009.

FOR FURTHER INFORMATION CONTACT: Alan Sinclair, FAA, Airframe/Cabin 
Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft 
Certification Service, 1601 Lind Avenue, SW., Renton, Washington, 
98057-3356; telephone (425) 227-2195; facsimile (425) 227-1232; 
electronic mail [email protected].

Background

    On July 1, 2008, Bombardier Inc. 400 Cote Vertu West, Dorval, 
Quebec, Canada, H4S 1Y9 applied for a design change to Type Certificate 
No. A21EA for installation of seats that include non-traditional, 
large, non-metallic panels in the following Bombardier Inc. airplanes: 
Model CL-600-2B19, Model CL-600-2C10, Model CL-600-2D15 and Model CL-
600-2D24. These airplanes, which are currently approved under Type 
Certificate No. A21EA, are swept-wing, T-tail, twin-engine, fuselage 
mounted turbofan-powered, single aisle, medium sized transport category 
airplanes.
    The applicable regulations to airplanes currently approved under 
Type Certificate No. A21EA do not require seats to meet the more 
stringent flammability standards required of large, non-metallic panels 
in the cabin interior. At the time the applicable rules were written, 
seats were designed with a metal frame covered by fabric, not with 
large, non-metallic panels. Seats also met the then recently adopted 
standards for flammability of seat cushions. With the seat design being 
mostly fabric and metal, the contribution to a fire in the cabin had 
been minimized and was not considered a threat. For these reasons, 
seats did not need to be tested to heat release and smoke emission 
requirements.
    Seat designs have now evolved to occasionally include non-
traditional, large, non-metallic panels. Taken in total, the surface 
area of these panels is on the same order as the sidewall and overhead 
stowage bin interior panels. To provide the level of passenger 
protection intended by the airworthiness standards, these non-
traditional, large, non-metallic panels in the cabin must meet the 
standards of Title 14 Code of Federal Regulations (14 CFR), part 25, 
Appendix F, parts IV and V, heat release and smoke emission 
requirements.

Type Certification Basis

    Under the provisions of Sec.  21.101 Bombardier must show that the 
following airplane models, CL-600-2B19, CL-600-2C10, CL-600-2D15 and 
CL-600-2D24, as changed, continue to meet the applicable provisions of 
the regulations incorporated by reference in Type Certificate No. 
A21AE, or the applicable regulations in effect on the date of 
application for the change. The regulations incorporated by reference 
in the type certificate are commonly referred to as the ``original type 
certification basis.''
    The regulations incorporated by reference in Type Certificate No. 
A21AE are for the following models:
     CL-600-2B19, part 25, effective February 1, 1965, 
including Amendments 25-1 through 25-62;
     CL-600-2C10, part 25, effective February 1, 1965, 
including Amendments 25-1 through 25-86:
     CL-600-2D15, part 25, effective February 1, 1965, 
including Amendments 25-1 through 25-86, Amendments 25-88 through 
Amendments 25-90 and Amendments 25-92 through Amendments 25-98.
     CL-600-2D24, part 25, effective February 1, 1965, 
including Amendments 25-1 through 25-86, Amendments 25-88 through 
Amendments 25-90 and Amendments 25-92 through Amendments 25-98.
    In addition, the certification basis includes other regulations and 
special conditions that are not pertinent to these special conditions.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for the Model CL-600 series airplanes 
because of a novel or unusual design feature, special conditions are 
prescribed under the provisions of 14 CFR 21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model CL-600 series airplanes must comply with the fuel 
vent and exhaust emission requirements of 14 CFR part 34 and the noise 
certification requirements of 14 CFR part 36.
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38 and they become part of the type 
certification basis under Sec.  21.17(a)(2).
    Special conditions are initially applicable to the model for which 
they

[[Page 44731]]

are issued. Should the type certificate for that model be amended later 
to include any other model that incorporates the same novel or unusual 
design feature, or should any other model already included on the same 
type certificate be modified to incorporate the same novel or unusual 
design feature, the special conditions would also apply to the other 
model under Sec.  21.101.

Novel or Unusual Design Features

    The Model CL-600 series airplanes will incorporate the following 
novel or unusual design features: These models offer interior 
arrangements that include passenger seats that incorporate non-
traditional, large, non-metallic panels in lieu of the traditional 
metal frame covered by fabric. The flammability properties of these 
panels have been shown to significantly affect the survivability of 
occupants of the cabin in the case of fire. These seats are considered 
a novel design for transport category airplanes that include Amendment 
25-61 and Amendment 25-66 in the certification basis, and were not 
considered when those airworthiness standards were established.
    The existing regulations do not provide adequate or appropriate 
safety standards for seat designs that incorporate non-traditional, 
large, non-metallic panels. In order to provide a level of safety that 
is equivalent to that provided by the balance of the cabin, additional 
airworthiness standards, in the form of special conditions, are 
necessary. These special conditions supplement 14 CFR 25.853. The 
requirements contained in these special conditions consist of applying 
the identical test conditions required of all other large panels in the 
cabin, to seats with non-traditional, large, non-metallic panels.

Definition of ``Non-Traditional, Large, Non-Metallic Panel''

    A non-traditional, large, non-metallic panel, in this case, is 
defined as a panel with exposed-surface areas greater than 1.5 square 
feet installed per seat place. The panel may consist of either a single 
component or multiple components in a concentrated area. Examples of 
parts of the seat where these non-traditional panels are installed 
include, but are not limited to: Seat backs, bottoms and leg/foot 
rests, kick panels, back shells, credenzas and associated furniture. 
Examples of traditional exempted parts of the seat include: Arm caps, 
armrest close-outs such as end bays and armrest-styled center consoles, 
food trays, video monitors and shrouds.

Clarification of ``Exposed''

    ``Exposed'' is considered to include those panels directly exposed 
to the passenger cabin in the traditional sense, plus those panels 
enveloped such as by a dress cover. Traditional fabrics or leathers 
currently used on seats are excluded from these special conditions. 
These materials must still comply with 14 CFR 25.853(a) and Sec.  
25.853(c) if used as a covering for a seat cushion, or Sec.  25.853(a) 
if installed elsewhere on the seat. Non-traditional, large, non-
metallic panels covered with traditional fabrics or leathers will be 
tested without their coverings or covering attachments.

Discussion

    In the early 1980s the FAA conducted extensive research on the 
effects of post-crash flammability in the passenger cabin. As a result 
of this research and service experience, we adopted new standards for 
interior surfaces associated with large surface area parts. 
Specifically, the rules require measurement of heat release and smoke 
emission (part 25, Appendix F, parts IV and V) for the affected parts. 
Heat release has been shown to have a direct correlation with post-
crash fire survival time. Materials that comply with the standards 
(i.e., Sec.  25.853 entitled ``Compartment interiors'' as amended by 
Amendment 25-61 and Amendment 25-66) extend survival time by 
approximately 2 minutes, over materials that do not comply.
    At the time these standards were written, the potential application 
of the requirements of heat release and smoke emission to seats was 
explored. The seat frame itself was not a concern because it was 
primarily made of aluminum and there were only small amounts of non-
metallic materials. It was determined that the overall effect on 
survivability was negligible, whether or not the food trays met the 
heat release and smoke requirements. The requirements, therefore, did 
not address seats. The preambles to both the Notice of Proposed Rule 
Making (NPRM), Notice No. 85-10 (50 FR 15038, April 16, 1985), and the 
Final Rule at Amendment 25-61 (51 FR 26206, July 21, 1986), 
specifically note that seats were excluded ``because the recently-
adopted standards for flammability of seat cushions will greatly 
inhibit involvement of the seats.''
    Subsequently, the Final Rule at Amendment 25-83 (60 FR 6615, March 
6, 1995) clarified the definition of minimum panel size: ``It is not 
possible to cite a specific size that will apply in all installations; 
however, as a general rule, components with exposed-surface areas of 
one square foot or less may be considered small enough that they do not 
have to meet the new standards. Components with exposed-surface areas 
greater than two square feet may be considered large enough that they 
do have to meet the new standards. Those with exposed-surface areas 
greater than one square foot, but less than two square feet, must be 
considered in conjunction with the areas of the cabin in which they are 
installed before a determination could be made.''
    In the late 1990s, the FAA issued Policy Memorandum 97-112-39, 
``Guidance for Flammability Testing of Seat/Console Installations,'' 
October 17, 1997. That memo was issued when it became clear that seat 
designs were evolving to include large non-metallic panels with surface 
areas that would impact survivability during a cabin fire event, 
comparable to partitions or galleys. The memo noted that large surface 
area panels must comply with heat release and smoke emission 
requirements, even if they were attached to a seat. If the FAA had not 
issued such policy, seat designs could have been viewed as a loophole 
to the airworthiness standards that would result in an unacceptable 
decrease in survivability during a cabin fire event.
    In October of 2004, an issue was raised regarding the appropriate 
flammability standards for passenger seats that incorporated non-
traditional, large, non-metallic panels in lieu of the traditional 
metal covered by fabric. The Seattle Aircraft Certification Office and 
Transport Standards Staff reviewed this design and determined that it 
represented the kind and quantity of material that should be required 
to pass the heat release and smoke emissions requirements. We have 
determined that special conditions would be promulgated to apply the 
standards defined in Sec.  25.853(d) to seats with large non-metallic 
panels in their design.

Discussion of Comments

    Notice of proposed special conditions no. 25-284-SC for the 
Bombardier Inc. Model CL-600-2B19, -2C10, -2D15 and -2D24 Airplanes was 
published in the Federal Register on June 5, 2009. No comments were 
received and the special conditions are adopted as proposed.

Applicability

    These special conditions are applicable to Bombardier model CL-600-
2B19 airplanes. Because the heat release testing requirements of Sec.  
25.853 per Appendix F, part IV are part of the type certification basis 
for airplane model CL-600-2B19, these special conditions are applicable 
to airplane

[[Page 44732]]

model CL-600-2B19. Although smoke testing requirements of Sec.  25.853 
per Appendix F, part V, are not part of the part 25 certification basis 
for Bombardier Model CL-600-2B19 airplanes, these special conditions 
are applicable if the airplanes are in 14 CFR part 121 service. Part 
121 requires applicable interior panels to comply with Sec.  25.853 and 
Appendix F, part V, regardless of the certification basis. It is not 
our intent to require seats with large non-metallic panels to meet 
Sec.  25.853 and Appendix F, parts V, if they are installed in cabins 
of airplanes that otherwise are not required to meet these standards. 
Should Bombardier apply at a later date for a change to the type 
certificate to include another model incorporating the same novel or 
unusual design feature, the special conditions would apply to that 
model as well.
    These special conditions are applicable to Bombardier airplane 
Models CL-600-2C10, -2D15 and -2D24. Because the heat release and smoke 
testing requirements of Sec.  25.853 are part of the type certification 
basis for the airplane Models CL-600-2C10, -2D15 and -2D24, these 
special conditions are applicable to the airplane Models CL-600-2C10, -
2D15 and -2D24. Should Bombardier apply at a later date for a change to 
the type certificate to include another model incorporating the same 
novel or unusual design feature, the special conditions would apply to 
that model as well.
    Seats do not have to meet these special conditions when installed 
in compartments that are not otherwise required to meet the test 
requirements of CFR part 25, Appendix F, parts IV and V. For example, 
airplanes that do not have Sec.  25.853, Amendment 25-61 or later, in 
their certification basis and those airplanes that do not need to 
comply with the requirements of Sec.  121.312.

Conclusion

    This action affects only certain novel or unusual design features 
on Bombardier Inc.: airplane Models CL-600-2B19, -2C10, -2D15 and -
2D24. It is not a rule of general applicability.
    The substance of these special conditions has been subjected to the 
notice and comment period in several prior instances and has been 
derived without substantive change from those previously issued. These 
special conditions were also subjected to a notice and comment period 
of 45 days with no changes made. Therefore, the FAA has determined that 
good cause exists for adopting these special conditions upon issuance.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

Authority Citation

0
The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701, 44702, 44704.

The Special Conditions

    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 Bombardier Inc. airplane Models CL-
600-2B19, -2C10, -2D15 and -2D24.
    1. Passenger Seats with Non-Traditional, Large, Non-metallic 
Panels.
    2. Except as provided in paragraph 3 of these special conditions, 
compliance with heat release and smoke emission testing requirements 
per 14 CFR part 25 and Appendix F, parts IV and V, is required for 
seats that incorporate non-traditional, large non-metallic panels that 
may either be a single component or multiple components in a 
concentrated area in their design.
    3. The applicant may designate up to and including 1.5 square feet 
of non-traditional, non-metallic panel material per seat place that 
does not have to comply with special condition Number 1, above. A 
triple seat assembly may have a total of 4.5 square feet excluded on 
any portion of the assembly (e.g., outboard seat place 1 square foot, 
middle 1 square foot, and inboard 2.5 square feet).
    4. Seats do not have to meet the test requirements of 14 CFR part 
25 and Appendix F, parts IV and V, when installed in compartments that 
are not otherwise required to meet these requirements. Examples 
include:
    a. Airplanes with passenger capacities of 19 or less,
    b. Airplanes that do not have 14 CFR 25.853, Amendment 25-61 or 
later, in their certification basis and do not need to comply with the 
requirements of 14 CFR 121.312, and
    c. Airplanes exempted from 14 CFR 25.853, Amendment 25-61 or later.
    5. Only airplanes associated with new seat certification programs 
approved after the effective date of these special conditions will be 
affected by the requirements in these special conditions. Previously 
certificated interiors on the existing airplane fleet and follow-on 
deliveries of airplanes with previously certificated interiors are not 
affected.

    Issued in Renton, Washington, on August 4, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20742 Filed 8-28-09; 8:45 am]
BILLING CODE 4910-13-P