- Effective
- April 12, 2000
- Issued
- February 24, 2000
- Model
- 407
- Data sheet
- TCDSH2SW
- Registered aircraft
- 986 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-11608
- Docket
- 98-SW-70-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.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 39 KB | 6048060f…2de3b7b | FAA DRS (API key needed) |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 407 helicopters, that requires modifying the door latch assemblies on all four crew and passenger doors. This amendment is prompted by an incident that occurred during a manufacturer's flight test, in which a door latch assembly broke, preventing occupants in the helicopter from opening the door. The actions specified by this AD are intended to prevent a door latch rod assembly from disengaging from the door handle and preventing helicopter occupants from opening the door
The airworthiness directive
2000-04-25 BELL HELICOPTER TEXTRON CANADA: Amendment 39-11068. Docket No. 98-SW-70-AD. Applicability: Model 407 helicopters, serial numbers 53000 through 53228, with door latch assemblies, part number (P/N) 20898-401, -402, -405, and -406, installed, certificated in any category.
NOTE 1: This AD applies to each helicopter 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 helicopters 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 within 100 hours time-in-service, unless accomplished previously.
To prevent a door latch rod assembly from disengaging from the door handle and preventing helicopter occupants from opening the door, accomplish the following:
(a) Modify each door latch assembly, P/N 20898-401, -402, -405, and -406, in accordance with the Accomplishment Instructions in Bell Helicopter Textron Alert Service Bulletin No. 407-98-18, dated May 27, 1998.
(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, Regulations Group, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with thisAD, if any, may be obtained from the Regulations Group.
(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 helicopter to a location where the requirements of this AD can be accomplished.
(d) The modification shall be done in accordance with Bell Helicopter Textron Alert Service Bulletin No. 407-98-18, dated May 27, 1998. 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 Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax (514) 433-0272. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on April 12, 2000.
NOTE 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-98-19, dated July 28, 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 AD that is applicable to BHTC Model 407 helicopters was published in the Federal Register on December 16, 1999 (64 FR 70201). That action proposed to require modifying the door latch assemblies on all four crew and passenger doors.
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 146 helicopters of U.S. registry will be affected by this AD, that it will take approximately 6 work hours per helicopter to accomplish the modification, and that the average labor rate is $60 per work hour. Required parts will cost approximately $210. Based on these figures, the total cost impactof the AD on U.S. operators is estimated to be $83,220.
The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.
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 thelocation 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 a new airworthiness directive 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 · 986
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1996 | 33 |
|---|---|
| 1997 | 56 |
| 1998 | 45 |
| 1999 | 31 |
| 2000 | 34 |
| 2001 | 26 |
| 2002 | 18 |
| 2003 | 24 |
| 2004 | 25 |
| 2005 | 26 |
| 2006 | 38 |
| 2007 | 35 |
| 2008 | 43 |
| 2009 | 24 |
| 2010 | 19 |
| 2011 | 24 |
| 2012 | 51 |
| 2013 | 54 |
| 2014 | 41 |
| 2015 | 37 |
| 2016 | 13 |
| 2017 | 5 |
| 2018 | 6 |
| 2019 | 27 |
| 2020 | 21 |
| 2021 | 34 |
| 2022 | 15 |
| 2023 | 28 |
| 2024 | 32 |
| 2025 | 25 |
| 2026 | 4 |
92 with no year recorded