[Federal Register Volume 60, Number 30 (Tuesday, February 14, 1995)]
[Rules and Regulations]
[Pages 8297-8298]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-1849]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-217-AD; Amendment 39-9128; AD 95-02-09]
Airworthiness Directives; British Aerospace Model ATP Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain British Aerospace Model ATP airplanes, that
requires inspections to detect damage, overheating, and proper
operation of the DC connections and cooling fans in certain transformer
rectifier units (TRU), and repair or replacement, if necessary. This
amendment is prompted by a report of the loss of all DC electrical
power, except for the battery emergency bus, due to failure of the
TRU's, which occurred during flight. The actions specified by this AD
are intended to prevent such failures that could lead to loss of
essential electrical power required to continue safe flight of the
airplane.
DATES: Effective March 16, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 16, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Jetstream Aircraft, Inc., P.O. Box 16029, Dulles
International Airport, Washington, DC 20041-6029. 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 Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 227-1320.
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 British Aerospace Model
ATP airplanes was published in the Federal Register on February 18,
1994 (59 FR 8145). That action proposed to require inspections of the
DC connections and cooling fans in certain transformer rectifier units
(TRU) to detect damage or overheating and to ensure correct operation,
and repair or replacement, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the rule.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this requirement.
Additionally, The FAA has recently reviewed the figures it has used
over the past several years in calculating the economic impact of AD
activity. In order to account for various inflationary costs in the
airline industry, the FAA has determined that it is necessary to
increase the labor rate used in these calculations from $55 per work
hour to $60 per work hour. The economic impact information, below, has
been revised to reflect this increase in the specified hourly labor
rate.
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 previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 10 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 2 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $1,200, or $120
per airplane.
The total 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.
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 [[Page 8298]] 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-02-09 British Aerospace (Commercial Aircraft), Limited:
Amendment 39-9128. Docket 93-NM-217-AD.
Applicability: Model ATP airplanes equipped with Ferranti
Transformer Rectifier Unit TR202A (Pt. No. 84/59100) or TR202B (Pt.
No. 84/60040), certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it 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 use the authority
provided in paragraph (b) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of essential electrical power required to
continue safe flight of the airplane, accomplish the following:
(a) Within 225 hours time-in-service after the effective date of
this AD, and thereafter at intervals not to exceed 625 hours time-
in-service, accomplish paragraphs (a)(1), (a)(2), (a)(3), and (a)(4)
of this AD.
(1) Perform a visual inspection of the DC connections to detect
any damage or overheating, in accordance with Ferranti Service
Bulletin 24-20-171, dated September 1993. If any damage or
overheating is found, prior to further flight, repair in accordance
with a method approved by Manager, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate.
(2) Perform a torque loading inspection of each DC connection to
ensure that torque loads are within the limits specified in Ferranti
Service Bulletin 24-20-171, dated September 1993; and, during this
inspection, ensure that each terminal stud is secure in its mounting
by visually observing that the stud does not rotate; in accordance
with Ferranti Service Bulletin 24-20-171, dated September 1993.
(3) Perform a visual inspection of the cooling fan blades to
detect any damage due to overheating, in accordance with Ferranti
Service Bulletin 24-20-172, dated September 1993. If any damage is
found, prior to further flight, replace the fan blade with a
serviceable part in accordance with the airplane maintenance manual.
(4) Perform a functional test of the operation of the cooling
fan by energizing the relay and confirming that cooling air exits
from the grill on top of the unit, in accordance with Ferranti
Service Bulletin 24-20-172, dated September 1993. Prior to further
flight, repair or replace any malfunctioning or damaged cooling fan
or cooling fan relay, in accordance with the airplane maintenance
manual.
(b) 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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) 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.
(d) The inspections and test shall be done in accordance with
Ferranti Service Bulletin 24-20-171, dated September 1993; and
Ferranti Service Bulletin 24-20-172, dated September 1993. 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 Jetstream Aircraft, Inc., P.O. Box
16029, Dulles International Airport, Washington, DC 20041-6029.
Copies may be inspected at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(e) This amendment becomes effective on March 16, 1995.
Issued in Renton, Washington, on January 19, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-1849 Filed 2-13-95; 8:45 am]
BILLING CODE 4910-13-P
