[Federal Register Volume 63, Number 55 (Monday, March 23, 1998)]
[Rules and Regulations]
[Pages 13773-13775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7381]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM146; Special Conditions No. 25-136-SC]


Special Conditions: McDonnell Douglas DC-10-10,-30 Airplane; High 
Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for McDonnell Douglas DC-
10-10,-30 airplanes modified by Innovative Solutions & Support, Inc. 
(IS&S). These airplanes will have novel and unusual design features 
when compared to the state of technology envisioned in the 
airworthiness standards for transport category airplanes. These special 
conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that provided by the existing airworthiness standards.

DATES: The effective date of these special conditions is March 9, 1998. 
Comments must be received on or before May 7, 1998.

ADDRESSES: Comments on these special conditions may be mailed in 
duplicate to: Federal Aviation Administration, Office of the Assistant 
Chief Counsel, Attn: Rules Docket (ANM-7), Docket No. NM146, 1601 Lind 
Avenue SW., Renton, Washington, 98055-4056; or delivered in duplicate 
to the Office of the Assistant Chief Counsel at the above address. 
Comments must be marked: Docket No. NM146. Comments may be inspected in 
the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. 
and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT: Greg Dunn, FAA, Standardization 
Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification 
Service, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; 
telephone (425) 227-2799; facsimile (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA has determined that good cause exists for making these 
special conditions effective upon issuance; however, interested persons 
are invited to submit such written data, views, or arguments as they 
may desire. Communications should identify the docket and special 
conditions number and be submitted in duplicate to the address 
specified above. All communications received on or before the closing 
date for comments will be considered by the Administrator. These 
special conditions may be changed in light of the comments received. 
All comments submitted will be available in the Rules Docket for 
examination by interested persons, both before and after the closing 
date for comments. A report summarizing each substantive public contact 
with FAA personnel concerning this rulemaking will be filed in the 
docket. Persons wishing the FAA to acknowledge receipt of their 
comments submitted in response to this request must submit with those 
comments a self-addressed, stamped postcard on which the following 
statement is made: ``Comments to Docket No. NM146.'' The postcard will 
be date stamped and returned to the commenter.

Background

    On July 15, 1997, Innovative Solutions & Support, Inc. applied for 
a supplemental type certificate (STC) to modify McDonnell Douglas DC-
10-10,-30 airplanes listed on Type Certificate A22WE. The modification 
incorporates the installation of a digital electronic altimeter for 
display of critical flight parameters (altitude) to the crew. These 
displays can be susceptible to disruption to both command/response 
signals as a result of electrical and magnetic interference. This 
disruption of signals could result in loss of all critical flight 
displays and annunciations or present misleading information to the 
pilot.

Type Certification Basis

    Under the provisions of 14 CFR Sec. 21.101, Innovative Solutions & 
Support, Inc. must show that the McDonnell Douglas DC-10-10,-30 
airplane, as changed, continues to meet the applicable provisions of 
the regulations incorporated by reference in Type certificate No. 
A22WE, 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

[[Page 13774]]

referred to as the ``original type certification basis.'' The 
certification basis for the modified McDonnell Douglas DC-10-10,-30 
airplane includes 14 CFR part 25, dated February 1, 1965, with 
Amendments 1 through 22 ``Airworthiness Standards: Transport Category 
Airplanes'', Sec. 25.471 of Amendment 25-23, part 36 ``Noise Standards: 
Aircraft Type Certification,'' Special Conditions No. 25-18-WE-7 dated 
January 7, 1970, Special Condition No. 25-18-WE-7, Amendment No. 1, 
dated July 9, 1971, and Special Condition No. 25-46-WE-14 dated October 
26, 1972.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 25, as amended) do not contain adequate or 
appropriate safety standards for the McDonnell Douglas DC-10-10,-30 
airplane because of novel or unusual design features, special 
conditions are prescribed under the provisions of Sec. 21.16 to 
establish a level of safety equivalent to that established in the 
regulations.
    Special conditions, as appropriate, are issued in accordance with 
14 CFR Sec. 11.49 after public notice, as required by Secs. 11.28 and 
11.29, and become part of the type certification basis in accordance 
with Sec. 21.101(b)(2).
    Special conditions are initially applicable to the model for which 
they are issued. Should Innovative Solutions & Support, Inc. apply at a 
later date for design change approval to modify any other model already 
included on the same type certificate to incorporate the same novel or 
unusual design feature, these special conditions would also apply to 
the other model under the provisions of Sec. 21.101(a)(1).

Novel or Unusual Design Features

    The modified McDonnell Douglas DC-10-10,-30 will incorporate a new 
electronic altimeter system that performs critical functions. This 
system may be vulnerable to HIRF external to the airplane.

Discussion

    There is no specific regulation that addresses protection 
requirements for electrical and electronic systems from HIRF. Increased 
power levels from ground-based radio transmitters and the growing use 
of sensitive electrical and electronic systems to command and control 
airplanes have made it necessary to provide adequate protection.
    To ensure that a level of safety is achieved equivalent to that 
intended by the regulations incorporated by reference, special 
conditions are needed for the McDonnell Douglas DC-10-10,-30, which 
require that new electrical and electronic systems, such as the EFIS, 
that perform critical functions be designed and installed to preclude 
component damage and interruption of function due to both the direct 
and indirect effects of HIRF.

High-Intensity Radiated Fields (HIRF)

    With the trend toward increased power levels from ground-based 
transmitters, plus the advent of space and satellite communications, 
coupled with electronic command and control of the airplane, the 
immunity of critical digital avionics systems to HIRF must be 
established.
    It is not possible to precisely define the HIRF to which the 
airplane will be exposed in service. There is also uncertainty 
concerning the effectiveness of airframe shielding for HIRF. 
Furthermore, coupling of electromagnetic energy to cockpit-installed 
equipment through the cockpit window apertures is undefined. Based on 
surveys and analysis of existing HIRF emitters, an adequate level of 
protection exists when compliance with the HIRF protection special 
condition is shown with either paragraphs 1, or 2 below:
    1. A minimum threat of 100 volts per meter peak electric field 
strength from 10 KHz to 18 GHz.
    a. The threat must be applied to the system elements and their 
associated wiring harnesses without the benefit of airframe shielding.
    b. Demonstration of this level of protection is established through 
system tests and analysis.
    2. A threat external to the airframe of the following field 
strengths for the frequency ranges indicated.

------------------------------------------------------------------------
                                                          Peak   Average
                       Frequency                         (V/M)     (V/M)
------------------------------------------------------------------------
10 KHz--100 KHz.......................................       50       50
100 KHz--500 KHz......................................       60       60
500 KHz--2 MHz........................................       70       70
2 MHz--30 MHz.........................................      200      200
30 MHz--100 MHz.......................................       30       30
100 MHz--200 MHz......................................      150       33
200 MHz--400 MHz......................................       70       70
400 MHz--700 MHz......................................    4,020      935
700 MHz--1 GHz........................................    1,700      170
1 GHz--2 GHz..........................................    5,000      990
2 GHz--4 GHz..........................................    6,680      840
4 GHz--6 GHz..........................................    6,850      310
6 GHz--8 GHz..........................................    3,600      670
8 GHz--12 GHz.........................................    3,500    1,270
12 GHz--18 GHz........................................    3,500      360
18 GHz--40 GHz........................................    2,100      750
------------------------------------------------------------------------

Applicability

    As discussed above, these special conditions are applicable to 
McDonnell Douglas DC-10-10,-30 airplanes modified by Innovative 
Solutions & Support. Should Innovative Solutions & Support, Inc. apply 
at a later date for design change approval to modify any other model 
included on the same type certificate to incorporate the same novel or 
unusual design feature, these special conditions would apply to that 
model as well under the provisions of Sec. 21.101(a)(1).

Conclusion

    This action affects only certain design features on McDonnell 
Douglas DC-10-10,-30 airplanes modified by Innovative Solutions & 
Support, Inc. It is not a rule of general applicability and affects 
only the applicant who applied to the FAA for approval of these 
features on the airplane.
    The substance of the special conditions for this airplane has been 
subjected to the notice and comment procedure in several prior 
instances and has been derived without substantive change from those 
previously issued. It is unlikely that prior public comment would 
result in a significant change from the substance contained herein. For 
this reason, and because a delay would significantly affect the 
certification of the airplane, which is imminent, the FAA has 
determined that prior public notice and comment are unnecessary and 
impracticable, and good cause exists for adopting these special 
conditions immediately. Therefore, these special conditions are being 
made effective upon issuance. The FAA is requesting comments to allow 
interested persons to submit views that may not have been submitted in 
response to the prior opportunities for comment described above.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

    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 McDonnell Douglas DC-10-10,-30 
airplanes modified by Innovative Solutions & Support, Inc. (IS&S).
    1. Protection from Unwanted Effects of High-Intensity Radiated 
Fields (HIRF). Each electrical and electronic system that performs 
critical functions must be designed and installed to ensure that the 
operation and operational capability of these systems to perform 
critical functions are not adversely affected when the airplane is

[[Page 13775]]

exposed to high intensity radiated fields.
    For the purpose of these special conditions, the following 
definition applies: Critical Functions. Functions whose failure would 
contribute to or cause a failure condition that would prevent the 
continued safe flight and landing of the airplane.

    Issued in Renton, Washington, on March 9, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service, ANM-100.
[FR Doc. 98-7381 Filed 3-20-98; 8:45 am]
BILLING CODE 4910-13-P