Airworthiness Directives; Honeywell IC-600 Integrated Avionics Computers, as Installed In, But Not Limited To, Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes

[Federal Register Volume 64, Number 5 (Friday, January 8, 1999)]
[Rules and Regulations]
[Pages 1110-1112]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-48]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-142-AD; Amendment 39-10979; AD 99-01-14]
RIN 2120-AA64


Airworthiness Directives; Honeywell IC-600 Integrated Avionics 
Computers, as Installed In, But Not Limited To, Empresa Brasileira de 
Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Honeywell IC-600 integrated avionics computers, 
that requires modification of the integrated avionics computers. This 
amendment is prompted by a report of integrated avionics computer 
failures, which caused a ``random reset'' condition of the electronic 
flight instrument system. The actions specified by this AD are intended 
to prevent such ``random reset'' conditions, which could affect the 
pilot's ability to control the airplane.

DATES: Effective February 12, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 12, 1999.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell Inc., Business and Commuter Aviation Systems, 
Box 29000, Phoenix, Arizona 85038. This information may be examined at 
the Federal Aviation Administration (FAA), Transport Airplane 
Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; 
or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: J. Kirk Baker, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane 
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount 
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5345; 
fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Honeywell IC-600 
integrated avionics computers was published in the Federal Register on 
June 3, 1998 (63 FR 30155). That

[[Page 1111]]

action proposed to require modification of the integrated avionics 
computers.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Limit Applicability

    One commenter requests that Learjet Model 45 airplanes be removed 
from the applicability of the proposed rule. The commenter indicates 
that there was only one Learjet Model 45 airplane with the suspect 
Honeywell IC-600 integrated avionics computer that received a standard 
certificate of airworthiness, and that airplane has been modified in 
accordance with the proposed rule.
    The FAA concurs with the commenter's request that the Learjet Model 
45 airplanes be removed from the applicability of the final rule. This 
decision is based on supporting documentation that there was only one 
Learjet Model 45 airplane with the suspect IC-600, and a modified IC-
600 was installed on that airplane before delivery to the customer. 
Furthermore, Learjet has incorporated the required modifications into 
production. The part numbers related to these airplanes will be removed 
from the appropriate sections in the final rule. The Summary and 
Applicability sections, as well as paragraph (b) of the final rule, 
have been revised accordingly.

Request To Reduce Compliance Time and Revise the Airplane Flight 
Manual

    One commenter requests that the compliance time for the 
modification in the proposed rule be reduced from 6 months to 30 days 
so that the unsafe condition is addressed in a more timely manner. The 
commenter also requests that a temporary revision to the FAA-approved 
Airplane Flight Manual (AFM) be issued in the interim to alert 
flightcrews of the potential hazards if the electronic flight 
instrument system fails. The commenter states that this is necessary 
because the unsafe condition exists today and the flightcrews may be 
unaware of the possibility of this potentially catastrophic condition.
    The FAA does not concur with the commenter's request. In developing 
an appropriate compliance time, the FAA considered the safety 
implications, parts availability, and normal maintenance schedules. 
Further, the compliance time of 6 months was established with the 
operator's, the manufacturer's, and FAA's concurrence. The FAA also has 
determined that, without prior notice and opportunity for public 
comment, a reduction in the compliance time is not appropriate. In 
light of these factors, and in consideration of the amount of time that 
has already elapsed since issuance of the proposed rule, the FAA has 
determined that further delay of this final rule is not warranted. 
However, if additional data are presented that would justify a 
reduction in the compliance time, the FAA may consider further 
rulemaking on this issue.
    With regard to the commenter's request for an AFM revision, the FAA 
has considered the potential hazard for temporary loss of flight 
guidance and does not consider that hazard to be catastrophic. The 
flightcrew's ability to use the standby instruments during the 30-
second rebuild of the display will allow them continued operational 
safety. Additionally, it was determined that at no time did the display 
present any hazardously misleading information. Therefore, the FAA does 
not find it appropriate to require a revision of the AFM. No change to 
the final rule is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 37 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 19 airplanes of U.S. registry 
will be affected by this proposed AD. It will take approximately 2 work 
hours per airplane to accomplish the required modification at an 
average labor rate of $60 per work hour. Required parts will be 
supplied by the manufacturer at no cost to operators. Based on these 
figures, the cost impact of the modification required by this AD on 
U.S. operators is estimated to be $2,280, or $120 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

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


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

99-01-14  Honeywell: Amendment 39-10979. Docket 98-NM-142-AD.

    Applicability: Honeywell IC-600 integrated avionics computers 
having part numbers 7017000-82401, -82402, -82403, -83401, -83402, 
and -83403, as installed in, but not limited to, EMBRAER Model EMB-
145 series airplanes.

    Note 1: This AD applies to Honeywell IC-600 integrated avionics 
computers having part numbers 7017000-82401, -82402, -82403, -83401, 
-83402, and -83403; as installed in any airplane, regardless of 
whether the airplane has been modified, altered, or repaired in the 
area subject to the requirements of this AD. For airplanes that have 
been modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (c)

[[Page 1112]]

of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent a ``random reset'' condition of the electronic flight 
instrument system, which could affect the pilot's ability to control 
the airplane, accomplish the following:
    (a) Within 6 months after the effective date of this AD, modify 
the IC-600 integrated avionics computer, in accordance with 
Honeywell Service Bulletin 7017000-22-43, dated March 24, 1998.
    (b) As of the effective date of this AD, no person shall install 
a Honeywell IC-600 integrated avionics computer having part number 
7017000-82401, -82402, -82403, -83401, -83402, or -83403 on any 
airplane; unless it has been modified in accordance with Honeywell 
Service Bulletin 7017000-22-43, dated March 24, 1998.
    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (e) The modification shall be done in accordance with Honeywell 
Service Bulletin 7017000-22-43, dated March 24, 1998. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Honeywell Inc., Business and 
Commuter Aviation Systems, Box 29000, Phoenix, Arizona 85038. Copies 
may be inspected at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or at the FAA, Transport 
Airplane Directorate, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (f) This amendment becomes effective on February 12, 1999.

    Issued in Renton, Washington, on December 28, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-48 Filed 1-7-99; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:54:23.401784+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

6cff49bd272532b27bae471e5a0aab0bd844c6ac0848c34d107e9ad20a24eaba

Text SHA-256

96aab2242cffd2497a20dcf9a6c0aa4b3c19163070cd0b38a1d03f9b89311104