[Federal Register Volume 60, Number 207 (Thursday, October 26, 1995)]
[Rules and Regulations]
[Pages 54799-54800]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-26557]



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 Rules and Regulations
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  Federal Register / Vol. 60, No. 207 / Thursday, October 26, 1995 / 
Rules and Regulations  

[[Page 54799]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-135-AD; Amendment 39-9416; AD 95-22-08]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain British Aerospace Model Viscount 744, 745D, 
and 810 airplanes, that currently establishes time-in-service limits 
for components of the fuselage pressure vessel, and requires 
modifications and inspections of various fuselage components to assure 
the continued structural integrity of these airplanes through the 
manufacturer's design life goal. This amendment requires additional 
modifications and inspections of the fuselage pressure vessel to extend 
the fuselage pressure vessel life from 30 to 45 years since new. This 
amendment is prompted by results of a review of fatigue test findings, 
stress analysis, and in-service history associated with pressure vessel 
components. The actions specified by this AD are intended to prevent 
reduced structural capability of the fuselage pressure vessel.

EFFECTIVE DATE: November 27, 1995.

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) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 65-20-04, 
amendment 39-3138 (23 FR 5506, February 9, 1978), which is applicable 
to certain British Aerospace Model Viscount 744, 745D, and 810 
airplanes, was published in the Federal Register on May 9, 1995 (60 FR 
24587). The action proposed to require various modifications and 
inspections of the fuselage pressure vessel to extend the fuselage 
pressure vessel life from 30 to 45 years since new.
    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.
    There are approximately 29 Model Viscount 744, 745D, and 810 series 
airplanes of U.S. registry will be affected by this AD.
    The actions that are currently required by AD 65-20-04 take 
approximately 200 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts cost approximately 
$37,000 per airplane. Based on these figures, the total cost impact on 
U.S. operators of the actions required by AD 65-20-04 is estimated to 
be $1,421,000, or $49,000 per airplane.
    The new actions that are required by this new AD will take 
approximately 400 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$37,400 per airplane. Based on these figures, the total cost impact on 
U.S. operators of the new requirements of this AD is estimated to be 
$1,780,600, or $61,400 per airplane.
    The total cost impact figures discussed above are 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, 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. 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-3138 (23 FR 
5506, February 9, 1978), and by adding a new airworthiness directive 
(AD), amendment 39-9416, to read as follows:

95-22-08  British Aerospace Regional Aircraft Limited (Formerly 
British Aerospace Commercial Aircraft Limited, Vicker-Armstrongs 
Aircraft Limited): Amendment 39-9416. Docket 94-NM-135-AD. 
Supersedes AD 65-20-04, Amendment 39-3138.

    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 

[[Page 54800]]
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) of this AD 
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 reduced structural capability of the fuselage 
pressure vessel, accomplish the following:
    (a) To operate the airplane for a maximum of 30 years since the 
date of manufacture or 75,000 total landings, whichever occurs 
first, accomplish the following:
    (1) Perform visual, eddy current, dye penetrant, and x-ray 
inspections in accordance with Sections 2 through 10 of British 
Aerospace Preliminary Technical Leaflet (PTL) No. 221, Issue 10, 
dated May 1, 1994 (for Model Viscount 744 and 745D airplanes); or 
PTL No. 94, Issue 10, dated September 1, 1993 (for Model Viscount 
810 airplanes); as applicable. Perform the initial inspection at the 
later of the times specified in paragraphs (a)(1)(i) and (a)(2)(ii) 
of this AD. Thereafter, repeat these inspections at the repetitive 
intervals specified in the applicable PTL.
    (i) Prior to the threshold specified in Sections 2 through 10 of 
the applicable PTL; or within the next repetitive inspection 
specified in Sections 2 through 10 of the applicable PTL following 
the immediately preceding inspection accomplished in accordance with 
PTL No. 221, Issue 4 (for Model Viscount 744 and 745D airplanes), or 
PTL No. 94, Issue 4 (for Model Viscount 810 airplanes); whichever 
occurs first. Or
    (ii) Within 60 days after the effective date of this AD.
    (2) Install the modifications specified in Sections 2 through 10 
of British Aerospace PTL No. 221, Issue 10, dated May 1, 1994 (for 
Model Viscount 744 and 745D airplanes); or PTL No. 94, Issue 10, 
dated September 1, 1993 (for Model Viscount 810 airplanes); as 
applicable. Accomplish this installation at the later of the times 
specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
    (i) Prior to the accumulation of the number of equivalent 
flights at 6.5 pounds per square inch (psi) specified in the initial 
compliance columns of Sections 2 through 10 of the applicable PTL. 
Or
    (ii) Within 60 days after the effective date of this AD.

    Note 2: The number of equivalent flights at 6.5 psi is 
determined by using the procedure specified in Section 1, Part 6, 
Paragraph 6.6, of PTL No. 221 or PTL No. 94, as applicable.

    (3) Modify the components of the pressurization system to reduce 
the cabin pressure maximum pressure setting to 3.5 psi, in 
accordance with Section 1, Part 7, Paragraph 7.5.2 of British 
Aerospace PTL No. 221, Issue 10, dated May 1, 1994 (for Model 
Viscount 744 and 745D airplanes); or PTL No. 94, Issue 10, dated 
September 1, 1993 (for Model Viscount 810 airplanes); as applicable. 
Accomplish this modification at the later of the times specified in 
paragraphs (a)(3)(i) and (a)(3)(ii) of this AD.
    (i) Prior to the accumulation of 25 years since date of 
manufacture, or prior to the accumulation of the number of flights 
equivalent to 17,000 flights at 6.5 psi; whichever occurs first. Or
    (ii) Within 30 days after the effective date of this AD.
    (b) This paragraph is applicable only to airplanes listed in 
British Aerospace PTL No. 320, Issue 3, dated October 1, 1993 (for 
Model Viscount 744 and 745 D airplanes); and PTL No. 189, Issue 5, 
dated May 1, 1994 (for Model Viscount 810 airplanes). To operate the 
airplane for a maximum of 45 years since date of manufacture or 
75,000 total landings, whichever occurs first: Prior to the 
accumulation of 30 years since date of manufacture, or within 2 
months after the effective date of this AD, whichever occurs later, 
perform the inspections, change the inspection times, install the 
modifications, and perform all other actions specified in the 
applicable PTL.
    (c) If any crack(s) or corrosion is found during any inspection 
required by this AD, prior to further flight, repair in accordance 
with British Aerospace PTL No. 221, Issue 10, dated May 1, 1994 (for 
Model 744 and 745D airplanes), or PTL No. 94, Issue 10, dated 
September 1, 1993 (for Model 810 airplanes).
    (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 
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.
    (f) This amendment becomes effective on November 27, 1995.

    Issued in Renton, Washington, on October 20, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-26557 Filed 10-25-95; 8:45 am]
BILLING CODE 4910-13-U