[Federal Register Volume 60, Number 39 (Tuesday, February 28, 1995)]
[Rules and Regulations]
[Pages 10807-10808]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3356]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-83-AD; Amendment 39-9144; AD 95-03-07]
Airworthiness Directives; Aerospatiale Model ATR72-101, -102, -
201, and -202 Series 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 Aerospatiale Model ATR72 series airplanes, that
requires an inspection to determine the model and orientation of
certain flight control rods, and replacement of the rods with modified
rods, if necessary. This amendment is prompted by reports of corrosion
found on the pitch and rudder trim and rudder travel limiter fail-safe
rods. The actions specified by this AD are intended to prevent problems
associated with corrosion of the flight control rods, which could
compromise the required strength of these items.
DATES: Effective March 30, 1995. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 30, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex
03, France. 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:
Sam Grober, Aerospace Engineer, Standardization Branch, ANM-113, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (206) 227-1187; 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 Aerospatiale Model ATR72
series airplanes was published in the Federal Register on July 27, 1994
(59 FR 38139). That action proposed to require an inspection to
determine the model and orientation of certain flight control rods, and
replacement of the rods with modified rods, if necessary. -
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
The FAA has determined that air safety and the public interest require
the adoption of the rule as proposed. -
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 effects 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. The FAA has
determined that this addition will neither increase the economic burden
on any operator nor increase the scope of the AD. -
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. -
The FAA estimates that 28 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 6 work hours per
airplane to accomplish the required inspection, 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 $10,080, or $360
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. -
Should replacement of any of the flight control rods be necessary,
the number of work hours and the cost of required parts will vary
according to the type of replacement accomplished. In a ``worst case
scenario'' (all subject rods needing replacement), the cost of parts
will be approximately $8,200 per airplane. Labor necessary to
accomplish replacement of a rod(s) will vary from 2 work hours to 10
work hours, at an average labor rate of $60 per work hour. -
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89. [[Page 10808]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-03-07 Aerospatiale: Amendment 39-9144. Docket 94-NM-83-AD.
Applicability: Model ATR72-101, -102, -201, and -202 series
airplanes; as listed in Aerospatiale Service Bulletin ATR72-27-1033,
dated February 23, 1994; 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 (d) 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 problems associated with corrosion of the flight
control rods, which could compromise the required strength of these
items, accomplish the following:
Note 2: Rods replaced and installed in accordance with the
instructions of any version of Aerospatiale Service Bulletin ATR72-
27-1010 prior to the effective date of this AD are not affected by
the requirements of this AD.
(a) For airplanes having Manufacturer's Serial Numbers (MSN) 126
through 183, inclusive: Within 18 months after the effective date of
this AD, visually inspect the elevator trim fail-safe rods to
determine the model and the orientation of the open end of the rod,
in accordance with Part A of Aerospatiale Service Bulletin ATR72-27-
1033, dated February 23, 1994.
(1) If a SARMA-type rod is installed, prior to further flight,
replace that rod with a modified rod, in accordance with
Aerospatiale Service Bulletin ATR72-27-1012, Revision 3, dated
October 7, 1991.
(2) If a TAC-type rod is installed, and if the open end of the
rod is oriented in any direction other than downwards, prior to
further flight, accomplish the reverse installation procedures
specified in Aerospatiale Service Bulletin ATR72-27-1010, Revision
4, dated February 23, 1994.
(b) For airplanes having MSN's 126 through 198 inclusive, 204,
and 207: Within 18 months after the effective date of this AD,
visually inspect the rudder trim fail-safe rods to determine the
model and the orientation of the open end of the rod, in accordance
with Part B of Aerospatiale Service Bulletin ATR72-27-1033, dated
February 23, 1994.
(1) If a SARMA-type rod is installed, prior to further flight,
replace that rod with a modified rod, in accordance with
Aerospatiale Service Bulletin ATR72-27-1012, Revision 3, dated
October 7, 1991.
(2) If a TAC-type rod is installed, and if the open end of the
rod is oriented in any direction other than downwards, prior to
further flight, accomplish the reverse installation procedures
specified in Aerospatiale Service Bulletin ATR72-27-1010, Revision
4, dated February 23, 1994.
(c) For airplanes having MSN's 198, and 126 through 237
inclusive: Within 18 months after the effective date of this AD,
visually inspect the rudder travel limitation unit fail-safe rods to
determine the model and the orientation of the open end of the rod,
in accordance with Part C of Aerospatiale Service Bulletin ATR72-27-
1033, dated February 23, 1994.
(1) If a SARMA-type rod is installed, prior to further flight,
replace that rod with a new rod in accordance with Aerospatiale
Service Bulletin ATR72-27-1027, dated July 28, 1993.
(2) If a TAC-type rod is installed at the rudder travel
limitation rod location, and if the open end of the rod is oriented
in any direction other than downwards, prior to further flight,
inspect that rod in accordance with Aerospatiale Service Bulletin
ATR72-27-1027, dated July 28, 1993.
(i) If no crack(s), deformation, or corrosion of the rod is
found, prior to further flight, reinstall the rod so that the open
end is oriented downwards, in accordance with the service bulletin.
(ii) If any crack(s), deformation, or corrosion of the rod is
found, prior to further flight, replace the rod with a modified rod
in accordance with the service bulletin.
(d) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(e) Special flight permits may be issued in accordance with
Secs. 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.
(f) The inspections, replacements, reverse installations, and
reinstallation shall be done in accordance with the following
Aerospatiale service bulletins, as applicable, which contain the
specified effective pages:
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Revision level
Service bulletin referenced and date Page No. shown on page Date shown on page
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ATR72-27-1012, Revision 3, October 7, 1991.... 1....................... 3............... Oct. 7, 1991.
2, 4, 6, 9.............. Original........ Oct. 29, 1990.
5, 7, 8................. 1............... Nov. 21, 1990.
3....................... 2............... May 16, 1991.
ATR72-27-1033 Original Issue, February 23, 1-10.................... Original........ Feb. 23, 1994.
1994.
ATR72-27-1027, Original Issue, July 28, 1993.. 1-11.................... Original........ July 28, 1993.
ATR72-27-1010, Revision 4, February 23, 1994.. 1, 3.................... 4............... Feb. 23, 1994.
2, 7.................... Original........ June 22, 1990.
4....................... 2............... Jan. 10, 1991.
5, 6.................... 1............... Nov. 21, 1990.
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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 Aerospatiale, 316 Route de Bayonne,
31060 Toulouse, Cedex 03, France. 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.
(g) This amendment becomes effective on March 30, 1995.
Issued in Renton, Washington, on February 6, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-3356 Filed 2-27-95; 8:45 am]
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