- Effective
- October 11, 1994
- Models
- BAe 146-100A, BAe 146-200A, BAe 146-300A
- Data sheet
- TCDSA49EU
- Registered aircraft
- 8 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-9009
- Docket
- 94-NM-42-AD
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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On this page
Summary
This amendment supersedes an existing airworthiness directive (AD), applicable to British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires replacing the quick release coupling halves on each end of the pump case drain line on the hydraulic engine driven pump (EDP) on the number 2 and number 3 engines with improved fire resistant coupling halves. This amendment revises the applicability of the existing AD. This amendment is prompted by the identification of additional airplanes that are subject to the addressed unsafe condition. The actions specified by this AD are intended to prevent hydraulic fluid leakage from the pump case drain line quick release coupling, which could fuel the flames in the event of an engine fire.
The airworthiness directive
94-17-14 BRITISH AEROSPACE: Amendment 39-9009. Docket 94-NM-42-AD. Supersedes AD 93-24-05, Amendment 39-8754. Applicability: Model BAe 146-100A series airplanes, serial numbers E1002 through E1199 inclusive; Model BAe 146-200A series airplanes, serial numbers E2008 through E2204 inclusive, and E2210 through E2220 inclusive; and Model BAe 146-300A series airplanes, serial numbers E3001 through E3219 inclusive, and E3222; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent hydraulic fluid leakage from the pump case drain line quick release couplings, which could fuel the flames in the event of an engine fire, accomplish the following:
(a) For airplane serial numbers E3001 through E3207 inclusive, E3209 through E3219 inclusive, and E3222: Within 6 months after January 20, 1994 (the effective date of AD 93-24-05, Amendment 39-8754), replace the quick release coupling halves on each end of the pump case drainline on the hydraulic engine driven pump (EDP) on the number 2 and number 3 engines with improved fire resistant coupling halves, in accordance with British Aerospace Service Bulletin SB.29-31-01339A, dated May 24, 1993, or SB.29-31-01339A, Revision 1, dated July 8, 1993.
(b) For airplane serial numbers E1002 through E1199 inclusive, E2008 through E2204 inclusive, E2210 through E2220 inclusive, and E3208: Within 6 months after the effective date of this AD, replace the quick release coupling halves on each end of the pump case drain line on the hydraulic EDP on the number 2 and number 3 engines with improved fire resistant coupling halves, in accordance with British Aerospace Service Bulletin SB.29-31-01339A, Revision 1, dated July 8, 1993.
(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 Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) The replacement shall be done in accordance with British Aerospace Service Bulletin SB.29-31-01339A, Revision 1, dated July 8, 1993, which includes the following list of effective pages:
Page Number Revision Level Shown on Page Date Shown on Page 1 1 July 8, 1993 2-11 Original (These pages are not dated)
This incorporation by reference is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The incorporation by reference of British Aerospace Service Bulletin SB.29-31-01339A, dated May 24, 1993, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of January 20, 1994 (58 FR 67310, December 21, 1993). Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. 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 October 11, 1994.
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 93-24-05, amendment 39-8754 (58 FR 67310, December 21, 1993), which is applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, was published in the Federal Register on May 12, 1994 (59 FR 24670). The action proposed to continue require replacement of the quick release coupling halves on each end of the pump case drain line on the hydraulic engine driven pump (EDP) on the number 2 and number 3 engines with improved fire resistant coupling halves, and proposed to revise the applicability of the existing AD to add additional airplanes.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on 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.
The FAA estimates that 46 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. Required parts will be provided by the manufacturer at no cost to operators. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $7,590, or $165 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.
39.13 - [Amended] 2. Section 39.13 is amended by removing amendment 39-8754 (58 FR 67310), and by adding a new airworthiness directive (AD), amendment 39-9009, to read as follows:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 8
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1985 | 1 |
|---|---|
| 1986 | 1 |
| 1987 | 1 |
| 1988 | 1 |
| 1989 | 2 |
2 with no year recorded