[Federal Register Volume 61, Number 37 (Friday, February 23, 1996)]
[Rules and Regulations]
[Pages 6921-6922]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-3976]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Parts 21 and 27

[Docket No. 93-ASW-2; Special Condition 27-ASW-1]


Special Condition: Eurocopter Deutschland Model EC135 Helicopter, 
Full Authority Digital Engine Control

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final special condition.

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SUMMARY: This special condition is issued for the Eurocopter 
Deutschland Model EC135 helicopter. This helicopter will have a novel 
or unusual design feature associated with the Turbomeca Arrius 2B or 
United Technologies Pratt & Whitney PW 206B engines with a full 
authority digital engine control (FADEC) system. This special condition 
contains additional safety standards that the Administrator considers 
necessary to establish a level of safety equivalent to that provided by 
the applicable airworthiness standards.

EFFECTIVE DATE: March 25, 1996.

FOR FURTHER INFORMATION CONTACT:
Mr. Carroll R. Wright, Federal Aviation Administration (FAA), 
Rotorcraft Standards Staff, Fort Worth, Texas 76193-0111; telephone 
(817) 222-5120.

SUPPLEMENTARY INFORMATION: 

Background

    Eurocopter Deutschland, Munich, Germany, submitted an application 
on October 31, 1990, for a Type Certificate for the Model BO-108 
(EC135) helicopter to the FAA Brussels Certification Office through the 
German Luftfahrt-Bundesamt Authorities (LBA). Notice of Proposed 
Special Condition 27-ASW-1 was published, based on this application, 
for protection of systems that perform critical functions from High 
Intensity Radiated Fields (HIRF). Due to delays and a redefinition of 
the proposed helicopter, a new application was submitted for Type 
Certification of the EC135 B-1 and D-1 helicopter on December 12, 1994, 
through the German LBA Authorities to the FAA Brussels Aircraft 
Certification Office. The Model EC135 is a 5-7 passenger, two engine, 
5,511-lb 

[[Page 6922]]
maximum take-off gross weight, normal category helicopter. This model 
helicopter may be equipped with either the Turbomeca Arrius 2B or the 
United Technologies Pratt & Whitney PW 206B engines. Both of these type 
engines utilize a FADEC system.

Type Certification Basis

    The certification basis established for the Model EC135 includes:
    1. 14 Code of Federal Regulations (CFR) 21.29.
    2. 14 CFR part 27, Amendment 30, dated October 3, 1994; and the 
following additional requirements to part 27, Amendment 30:
    a. Section 27.65 with the following changes: the introductory 
portion of Sec. 27.65(b)(2) is changed to read ``The steady rate of 
climb must be determined,'' and Sec. 27.65(b)(2)(ii) is changed to read 
``Within the range from sea level up to the maximum altitude for which 
certification is requested.''
    b. Section 27.1141 plus a new requirement that ``Each control must 
be able to maintain any set position without (1) Constant attention; or 
(2) Tendency to creep due to control loads or vibration.''
    c. Additional requirements for rotor brake controls state that (1) 
It must be impossible to apply the rotor brake inadvertently in flight, 
and (2) There must be means to warn the crew if the rotor brake has not 
been completely released before takeoff.''
    3. Applicable paragraphs of part 29, Amendment 36, dated January 
31, 1996; as follows: 29.861(a), 29.901(c), 29.903 (b), (c), (e), 
29.908(a), 29.917(b), (c)(1), 29.927(c)(1), 29.953(a), 29.1027(a), 
20.1045(a)(1), (b), (c), (d), (f), 29.1047(a), 29.1181(a), 29.1189(c), 
29.1191(a)(1), 29.1193(e), 29.1305(a)(6), (b), 29.1309(b)(2)(i), (d), 
29.1331(b), 29.1351(d)(2).
    4. Noise Requirements of part 36 Noise Standards Appendix J amended 
by Amendments 36-1 through the latest amendment in effect at the time 
of certification.
    If the Administrator finds that the applicable airworthiness 
regulations do not contain adequate or appropriate safety standards for 
the Model EC135 helicopter because of a novel or unusual design 
feature, special conditions are prescribed under the provisions of 
Sec. 21.101(b)(2) establish a level of safety equivalent to that 
established in the regulations.
    Special conditions, as appropriate, are issued in accordance with 
Sec. 11.49 after public notice, as required by Secs. 11.28 and 11.29(b) 
and become a part of the type certification basis, as provided by 
Sec. 21.101(b)(2). In addition to the applicable airworthiness 
regulations and special conditions, the Model EC135 helicopter must 
comply with the noise certification requirements of part 36 and the 
engine emission requirements of Special Federal Aviation Regulation 
(SFAR) 27.

Discussion of Comments

    Notice of Proposed Special Condition No. SC-93-SW was published in 
the Federal Register on January 22, 1993 (58 FR 5666). Two comments 
were received from the manufacturer. One comment corrected the name of 
the manufacturer. The other comment stated that the laboratory test 
option should satisfy this special condition for VFR including 
operation below 500 feet AGL. The FAA agrees with both comments. The 
name is corrected in this final special condition, and the other 
comment does not require a change to the rule as proposed. Therefore, 
except for the name change, the special condition is adopted as 
proposed.
    Special conditions are initially applicable to the model for which 
they 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 the provisions of Sec. 21.101(a)(1).

Novel or Unusual Design Feature

    The Eurocopter Deutschland Model EC135 helicopter has been 
identified as incorporating one and possibly more electrical or 
electronic systems that will be performing functions critical to the 
continued safe flight and landing of the helicopter. FADEC is an 
electronic device that performs the critical functions of engine 
control. The control of the engines is critical to the continued safe 
flight and landing of the helicopter during visual flight rules (VFR) 
and instrument flight rules (IFR) operations.
    If it is determined that this helicopter will incorporate other 
electrical or electronic systems performing critical functions, those 
systems also will be required to comply with the requirements of this 
special condition.
    As discussed above, these special conditions are applicable 
initially the Model EC135 helicopter. Should Eurocopter Deutschland 
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, under the 
provisions of Sec. 21.101(a)(1).

Conclusion

    This action affects only one unusual or novel design feature on one 
series of helicopters. It is not a rule of general applicability and 
affects only the manufacturer who applied to the FAA for approval of 
these features on the affected helicopter.

List of Subjects in 14 CFR Parts 21 and 27

    Aircraft, Air transportation, Aviation safety, Rotorcraft, Safety.

    The authority citation for this special condition is as follows:

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

The Special Condition

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special condition is issued as part of the 
type certification basis for the Eurocopter Deutschland Model EC-135 
helicopter.

Protection for Electrical/Electronic Systems From High Intensity 
Radiated Fields.

    Each system that performs critical functions must be designed and 
installed to ensure that the operation and operational capabilities of 
these critical functions are not adversely affected when the helicopter 
is exposed to high intensity radiated fields external to the 
helicopter.

    Issued in Fort Worth, Texas, on February 9, 1996.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-3976 Filed 2-22-96; 8:45 am]
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