[Federal Register Volume 59, Number 218 (Monday, November 14, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27969]


[[Page Unknown]]

[Federal Register: November 14, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-109-AD]

 

Airworthiness Directives; British Aerospace Model Viscount 744, 
745D, and 810 Series Airplanes.

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all British Aerospace Model 
Viscount 744, 745D, and 810 series airplanes. This proposal would 
require 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 proposal is 
prompted by a reported failure of a pivot pin due to fatigue cracking. 
The actions specified by the proposed AD are intended to prevent 
failure of the pivot pin, which could result in the loss of nose wheel 
steering capability.

DATES: Comments must be received by December 27, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-109-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from British Aerospace, The Military Business Unit (M.B.U.), 
In-Service Aircraft, Greengate, Middleton, Manchester M24.1SA, England. 
This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-109-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs.

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 94-NM-109-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority, which is the airworthiness authority 
for the United Kingdom, recently notified the FAA that an unsafe 
condition may exist on all British Aerospace Model Viscount 744, 745D 
and 810 series airplanes. The CAA advises of a report of failure of the 
pivot pin that attaches one of the two nose wheel steering actuators to 
the steering head assembly on the nose undercarriage leg. The failure 
of the pin has been attributed to fatigue cracking. This condition, if 
not detected and corrected in a timely manner, could result in loss of 
nose wheel steering capability.
    British Aerospace has issued Viscount Preliminary Technical Leaflet 
(PTL) 334, Issue 2 (for the Model 744 and 745D series airplanes), and 
PTL 205, Issue 2 (for the Model 810 series airplanes), both dated July 
8, 1994. These PTL's describe procedures for 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. The CAA classified these 
PTL's as mandatory in order to assure the continued airworthiness of 
these airplanes in the United Kingdom.
    This airplane model is manufactured in the United Kingdom and is 
type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral airworthiness agreement, the CAA has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would 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. The actions 
would be required to be accomplished in accordance with the PTL's 
described previously.
    The FAA estimates that 29 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours per airplane, per inspection cycle, 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 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 proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ``ADDRESSES.''

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

British Aerospace Regional Aircraft Limited (Formerly British 
Aerospace Commercial Aircraft Limited, Vickers-Armstrongs Aircraft 
Limited): Docket 94-NM-109-AD.

    Applicability: All Model Viscount 744, 745D, and 810 series 
airplanes, certificated in any category.
    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: 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.

    Issued in Renton, Washington, on November 7, 1994.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-27969 Filed 11-10-94; 8:45 am]
BILLING CODE 4910-13-U