[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-M
