- Effective
- December 17, 1998
- Published
- November 12, 1998 · 63 FR 63130–63132
- Models
- Viscount 744, Viscount 745D, Viscount 810
- Data sheet
- TCDSA-814
- Product
- Aircraft · Large airplane
- Amendment
- 39-10880
- Docket
- 98-NM-217-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. Only the govinfo PDF is the legal edition. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 124 KB | 365d3165…d73a84a | 98-30053.pdf on govinfo.gov |
| FAA DRS HTML | 59 KB | 95c57364…2548ff5 | FAA DRS (API key needed) |
| Federal Register text | 13 KB | 8a274d76…33dcf3c | 98-30053.txt on federalregister.gov |
On this page
Summary
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model Viscount 700, 800, and 810 series airplanes, that currently requires repetitive inspections to detect cracks and corrosion in the inboard and outboard engine nacelle structures on the wings; replacement of any cracked fittings and mating struts; and treatment or replacement of any corroded fittings or struts. This amendment requires repetitive inspections to detect cracking or corrosion of the eye end fittings of the outboard engine lower support or of the bore of the taper pin holes, and repair, if necessary. This amendment also limits the applicability of the existing AD. This amendment is prompted by reports of cracked and separated lower eye end fittings. The actions specified by this AD are intended to detect and correct cracking of the eye end fittings of the outboard engine lower support, which could result in reduced structural integrity of the engine nacelle support structures.
The airworthiness directive
98-23-13 BRITISH AEROSPACE REGIONAL AIRCRAFT LIMITED (Formerly British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs Aircraft Limited): Amendment 39-10880. Docket 98-NM-217-AD. Supersedes AD 90-20-17, amendment 39-6744. Applicability: Model Viscount 744, 745, and 745D series airplanes, on which British Aerospace Modification D3227 has not been accomplished; and Model Viscount 810 series airplanes, on which British Aerospace Modification FG 2103 has not been accomplished; certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To detect and correct cracking of the eye end fittings of the outboard engine lower support, which could result in reduced structural integrity of the engine nacelle support structures, accomplish the following:
(a) Perform an eddy current inspection to detect cracking or corrosion of the eye end fittings of the outboard engine lower support, or of the bore of the taper pin holes, in accordance with the Accomplishment Instructions of British Aerospace Preliminary Technical Leaflet (PTL) No. 326, Issue 2, including Appendices 1 and 2, all dated December 1, 1994 (for Model Viscount 744, 745, and 745D series airplanes); or PTL 197, Issue3, including Appendices 1 and 2, all dated November 20, 1993 (for Model Viscount 810 series airplanes); at the applicable time specified in either paragraph (a)(1) or (a)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 900 landings.
(1) For Model Viscount 744, 745, and 745D series airplanes: Inspect within 3 months after the effective date of this AD.
(2) For Model Viscount 810 series airplanes: Inspect within 900 landings after the last inspection performed in accordance with PTL 197, Issue 2, dated July 10, 1992; or within 3 months after the effective date of this AD; whichever occurs later.
(b) If any cracking is found during any inspection performed in accordance with paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority (or its delegated agent).
(c) An alternative method ofcompliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
(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 shall be done in accordance with the following British Aerospace Regional Aircraft Preliminary Technical Leaflets, which contain the specified effective pages:
Preliminary Technical Leaflet Referenced and Date
Page Number Shown on Page
Revision Level Shown on Page
Date Shown on Page
PTL 326, Issue 2, December 1, 1994 1-6
2
December 1, 1994
APPENDIX 1 1-6 2 December 1, 1994
APPENDIX 2 1-6 2 December 1, 1994
_______________________________________________________________________________
Preliminary Technical Leaflet Referenced and Date
Page Number Shown on Page
Revision Level Shown on Page
Date Shown on Page
PTL 197, Issue 3, November 20, 1993 1-8
3
November 20, 1993
APPENDIX 1 1-6 3 November 20, 1993
APPENDIX 2 1-7 Original November 20, 1993
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 Limited, Chadderton Division, Engineering Support, Greengate, Middleton, Manchester M24 1SA, England. Copiesmay 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 December 17, 1998.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 90-20-17, amendment 39-6744 (55 FR 38539, September 19, 1990), which is applicable to all British Aerospace Model Viscount 700, 800, and 810 series airplanes, was published in the Federal Register on September 8, 1998 (63 FR 47440). The action proposed to require new repetitive inspections to detect cracking or corrosion of the eye end fittings of the outboard engine lower support or of the bore of the taper pin holes, and repair, if necessary. The action also proposed to limit the applicability of the existing AD.
Comments 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.
Conclusion The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
Cost Impact There are approximately 29 airplanes of U.S. registry that will be affected by this AD.
The new eddy current inspections that are required in this AD take approximately 2 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspections required by this AD on U.S. operators is estimated to be $3,480, or $120 per airplane, per inspection cycle.
The 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.
Regulatory Impact 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 withExecutive 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 meby 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), 40113, 44701.
39.13 [Amended] 2. Section 39.13 is amended by removing amendment 39-6744 (55 FR 38539, September 19, 1990), and by adding a new airworthiness directive (AD), amendment 39-10880, to read as follows:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.