[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]
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