[Federal Register Volume 60, Number 19 (Monday, January 30, 1995)]
[Rules and Regulations]
[Pages 5568-5570]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-2154]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-104-AD; Amendment 39-9111; AD 94-26-16]
Airworthiness Directives; British Aerospace Model Viscount 744,
745D, and 810 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 all British Aerospace Model Viscount 744, 745D, and 810
series airplanes, that requires various inspections to detect damage,
corrosion, or cracking of certain taper plugs and split bushings of the
engine mount, and replacement of taper plugs or split bushings with
serviceable parts, if necessary. This amendment is prompted by a report
of damage of the taper plug and split bushing of the engine mount due
to the effects of corrosion. The actions specified by this AD are
intended to prevent such damage, which could lead to failure of the
engine mount attachment assembly and consequent separation of the
engine from the airplane.
DATES: Effective March 1, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 1, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from British Aerospace Regional Aircraft Ltd., Engineering
Support Manager, Military Business Unit, Chadderton Works, Greengate,
Middleton, Manchester M24 1SA, England. 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 all British Aerospace Model
Viscount 744, 745D, and 810 series airplanes was published in the
Federal Register on September 14, 1994 (59 FR 47101). That action
proposed to require detailed visual and nondestructive test (NDT)
inspections to detect damage, corrosion, or cracking of certain taper
plugs and split bushings of the engine mount, and replacement of
discrepant parts.
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 proposed 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.
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 comment
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 25 Model Viscount 744 and 745D series
airplanes [[Page 5569]] of U.S. registry will be affected by this AD,
that it will take approximately 25 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 of these airplanes is estimated to be $37,500, or
$1,500 per airplane.
The FAA estimates that 4 Model Viscount 810 series airplanes of
U.S. registry will be affected by this AD, that it will take
approximately 25 work hours per airplane to accomplish the proposed
actions, and that the average labor rate is $60 per work hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators of these airplanes is estimated to be $6,000, or $1,500 per
airplane.
Based on the above figures, the total cost impact of the actions
proposed by this AD on U.S. operators is estimated to be $43,500, or
$1,500 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 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:
94-26-16 British Aerospace Regional Aircraft Limited (Formerly
British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs
Aircraft Limited): Amendment 39-9111. Docket 94-NM-104-AD.
Applicability: All Model Viscount 744, 745D, and 810 series
airplanes, 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 (c) 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 separation of the engine from the airplane,
accomplish the following:
(a) At the next unscheduled engine removal, but no later than 12
months after the effective date of this AD, perform a detailed
visual inspection to detect damage, corrosion, or cracking of taper
plugs, having part number (P/N) 60216-1017, and split bushings
(bushes), having P/N 60216-1019, of the engine mount, in accordance
with British Aerospace Viscount Preliminary Technical Leaflet (PTL)
200, Disc.9 Doc.5, dated December 6, 1991 (for Model Viscount 810
series airplanes); or British Aerospace Viscount PTL 329, Disc.9
Doc.2, dated April 1, 1992 (for Model Viscount 744 and 745D series
airplanes); as applicable.
(1) If no taper plugs or split bushings are damaged, corroded,
or cracked, repeat the inspection thereafter at each unscheduled
engine removal, but no later than 48 months after the last visual
inspection of the taper plugs and split bushings.
(2) If any taper plug or split bushing is damaged, corroded, or
cracked, prior to further flight, replace the taper plug or split
bushing with a serviceable part, in accordance with the applicable
PTL. Thereafter, repeat the inspection at each unscheduled engine
removal, but no later than 48 months after the last visual
inspection of the taper plugs and split bushings.
(b) At the next scheduled engine removal, but no later than 12
months after the effective date of this AD, perform detailed visual
and nondestructive test (NDT) inspections to detect damage,
corrosion, or cracking of all taper plugs and split bushings of the
engine mount, in accordance with British Aerospace Viscount PTL 200,
Disc.9 Doc.5, dated December 6, 1991 (for Model Viscount 810 series
airplanes); or British Aerospace Viscount PTL 329, Disc.9 Doc.2,
dated April 1, 1992 (for Model Viscount 744 and 745D series
airplanes); as applicable.
(1) If no taper plug or split bushing is damaged, corroded, or
cracked, repeat the visual and NDT inspections thereafter at each
scheduled engine removal, but no later than 48 months after the last
visual and NDT inspections of the taper plugs and split bushings.
(2) If any taper plug or split bushing is damaged, corroded, or
cracked, prior to further flight, replace the taper plug or split
bushing with a serviceable part, in accordance with the applicable
PTL. Thereafter, repeat the visual and NDT inspections at each
scheduled engine removal, but no later than 48 months after the last
visual and NDT inspections of the taper plugs and split bushings.
(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, 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.
(d) Special flight permits may be issued in accordance
Secs. 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 inspections and replacements shall be done in accordance
with British Aerospace Viscount Preliminary Technical Leaflet (PTL)
200, Disc.9 Doc.5, dated December 6, 1991 (for Model Viscount 810
series airplanes); or British Aerospace Viscount PTL 329, Disc.9
Doc.2, dated April 1, 1992 (for Model Viscount 744 and 745D series
airplanes); as applicable. 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
British Aerospace Regional Aircraft Ltd., [[Page 5570]] Engineering
Support Manager, Military Business Unit, Chadderton Works,
Greengate, Middleton, Manchester M24 1SA, England. 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.
(f) This amendment becomes effective on March 1, 1995.
Issued in Renton, Washington, on December 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-2154 Filed 1-27-95; 8:45 am]
BILLING CODE 4910-13-U
