- Effective
- July 15, 1998
- Published
- June 10, 1998 · 63 FR 31608–31609
- Model
- ATP
- Data sheet
- TCDSA27NM
- Product
- Aircraft · Large airplane
- Amendment
- 39-10581
- Docket
- 98-NM-53-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 | 118 KB | 3f938a41…8acd97c | 98-15253.pdf on govinfo.gov |
| FAA DRS HTML | 49 KB | 036c9d82…9333808 | FAA DRS (API key needed) |
| Federal Register text | 10 KB | c40350cb…2b11c0a | 98-15253.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive magnetic particle inspections to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the splined operating shaft of the internal door handle, which could result in failure of the internal door handle, inability to operate the door during an emergency evacuation, and consequent injury to airplane occupants.
The airworthiness directive
98-12-27 BRITISH AEROSPACE REGIONAL AIRCRAFT [Formerly Jetstream Aircraft Limited; British Aerospace (Commercial Aircraft) Limited]: Amendment 39-10581. Docket 98-NM-53-AD. Applicability: BAe Model ATP airplanes, constructor s numbers 2002 through 2067 inclusive; 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 request approval for an alternative method of compliance in accordance with paragraph (b) 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 includespecific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To detect and correct cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door, which could result in failure of the internal door handle, inability to operate the door during an emergency evacuation, and consequent injury to airplane occupants; accomplish the following:
(a) Prior to the accumulation of 2,000 flight cycles on the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; or within 60 days after the effective date of this AD; whichever occurs later: Accomplish either paragraph (a)(1) or (a)(2) of this AD.
(1) Perform a magnetic particle inspection to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door, in accordance with British Aerospace Regional Aircraft BAe ATP Alert Service Bulletin ATP-A52-30, dated March 19, 1997.
(i) If any crack is found, prior to further flight, accomplish the actions required by paragraph (a)(2).
(ii) If no crack is found, repeat the actions required by paragraph (a) of this AD at intervals not to exceed 1,000 flight cycles.
(2) Replace the existing splined operating shaft with a new splined operating shaft, in accordance with the alert service bulletin. Repeat the actions required by paragraph (a) of this AD within 2,000 flight cycles after the replacement, and thereafter at intervals not to exceed 1,000 flight cycles.
(b) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their request through an appropriate FAA PrincipalMaintenance 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.
(c) 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.
(d) The actions shall be done in accordance with British Aerospace Regional Aircraft BAe ATP Alert Service Bulletin ATP-A52-30, dated March 19, 1997. 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 AI(R) American Support, Inc., 13850 McLearen Road, Herndon, Virginia 20171. 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.
NOTE 3: The subject of this AD is addressed in British airworthiness directive 004-03-97.
(e) This amendment becomes effective on July 15, 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) to include an airworthiness directive (AD) that is applicable to certain British Aerospace BAe Model ATP airplanes was published in the Federal Register on April 9, 1998 (63 FR 17342). That action proposed to require repetitive magnetic particle inspections to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; and corrective actions, if necessary.
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 The FAA estimates that 10 airplanes of U.S. registry will be affected by this AD, that it will take approximately 18 work hours per airplane to accomplish the required magnetic particle inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the magnetic particle inspection required by this AD on U.S. operators is estimated to be $10,800, or $1,080 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 with Executive Order 12612, it is determined that this final rule does not have sufficient federalismimplications 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. 106(g), 40113, 44701.
39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.