[Federal Register Volume 60, Number 32 (Thursday, February 16, 1995)]
[Rules and Regulations]
[Pages 8929-8930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3245]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-109-AD; Amendment 39-9141; AD 95-03-04]


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 repetitive inspections to detect 
fatigue cracking in the pivot pins that attach both nose wheel steering 
actuators to the steering head assembly, and replacement of cracked 
pins. This amendment is prompted by a reported failure of a pivot pin 
due to fatigue cracking. The actions specified by this AD are intended 
to prevent failure of the pivot pin, which could result in the loss of 
nose wheel steering capability.

DATES: Effective March 20, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 20, 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 November 14, 1994 (59 FR 56435). That action 
proposed to require initial and repetitive magnetic particle 
inspections to detect cracking of the pivot pin that attaches the nose 
wheel steering actuators to the steering head assembly, and replacement 
of cracked pins.
    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.
    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 determined that this addition will neither increase the 
economic burden on any operator nor increase the scope of the AD.
    The FAA estimates that 29 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 3 work hours per 
airplane, per inspection cycle, 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 $5,220, or $180 per airplane, per inspection cycle.
    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:

    [[Page 8930]] 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:

95-03-04  British Aerospace Regional Aircraft Limited (Formerly 
British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs 
Aircraft Limited): Amendment 39-9141. Docket 94-NM-109-AD.

    Applicability: All Model Viscount 744, 745D, and 810 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 loss of nose wheel steering capability due to failure 
of the pivot pin, accomplish the following:
    (a) Prior to the accumulation of 1,100 landings after the 
effective date of this AD, or within 14 months after the effective 
date of this AD, whichever occurs first, perform a magnetic particle 
inspection to detect cracks of the nose wheel steering actuators 
connecting (pivot) pins, in accordance with either Viscount 
Preliminary Technical Leaflet (PTL) 334, Issue 2, dated July 8, 1992 
(for Model 744 and 745D series airplanes); or Viscount PTL 205, 
Issue 2, dated July 8, 1992 (for Model 810 series airplanes); as 
applicable. Repeat this inspection thereafter at intervals not to 
exceed 1,100 landings or 14 months, whichever occurs first.
    (b) If any crack is found in a pivot pin during any inspection 
required by this AD, replace the pivot pin in accordance with either 
Preliminary Technical Leaflet (PTL) 334, Issue 2, dated July 8, 1992 
(for Model 744 and 745D series airplanes), or Viscount PTL 205, 
Issue 2, dated July 8, 1992 (for Model 810 series airplanes). After 
replacement, repeat the inspection required by paragraph (a) of this 
AD at intervals not to exceed 1,100 landings or within 14 months, 
whichever occurs first.
    (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 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 inspections and replacement shall be done in accordance 
with Viscount PTL 334, Issue 2, dated July 8, 1992; or Viscount PTL 
205, Issue 2, dated July 8, 1992; 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., 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 20, 1995.

    Issued in Renton, Washington, on February 3, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-3245 Filed 2-15-95; 8:45 am]
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