- Effective
- September 10, 2001
- Published
- August 6, 2001 · 66 FR 40867–40869
- Issued
- July 25, 2001
- Models
- Hawker 800 (U-125A), Hawker 800XP
- Data sheet
- TCDSA3EU
- Registered aircraft
- 284 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-12360
- Docket
- 2000-NM-274-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 01-19251. Only the govinfo PDF is the legal edition. DRS record last changed January 21, 2026.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 141 KB | 02f56bf0…cfb43f0 | 01-19251.pdf on govinfo.gov |
| Federal Register XML | 14 KB | 50ddfba3…5875643 | 01-19251.xml on federalregister.gov |
| FAA DRS HTML | 46 KB | 4287c31d…a3754f3 | FAA DRS (API key needed) |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP series airplanes and certain Model Hawker 800 (U-125A military) airplanes, that requires a one-time inspection of an attachment bolt in the main landing gear (MLG) door system to determine whether the bolt's protruding threads have been peened; and corrective action, if necessary. The actions specified by this AD are intended to prevent the disconnection of the retaining hook (which holds the MLG door up and locked) from its means of actuation, which could result in a gear-up landing and possible injury to passengers and crew. This action is intended to address the identified unsafe condition.
The airworthiness directive
2001-15-25 Raytheon Aircraft Company: Amendment 39-12360. Docket 2000-NM-274-AD.
Applicability: Model Hawker 800XP series airplanes, and Model Hawker 800 (U-125A military) airplanes; certificated in any category; as listed in Raytheon Service Bulletin SB 32-3386, dated June 2000.
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 include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent a main landing gear (MLG) gear-up landing and possible injury to passengers and crew, accomplish the following:
(a) Inspection and Corrective Action
PDF page 2(a) Within 100 flight hours after the effective date of this AD: Perform a general visual inspection of the MLG attachment bolt at the interface between the right and left MLG door retaining hooks and the uplock spring struts to determine whether the bolt's protruding threads next to the nuts have been peened, in accordance with Raytheon Service Bulletin SB 32-3386, dated June 2000. If the threads have not been peened, prior to further flight, peen the threads in accordance with the service bulletin.
Note 2:
For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
(b) Alternative Methods of Compliance
PDF page 2(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, Wichita Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.
Note 3:
Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.
(c) Special Flight Permits
PDF page 2(c) Special flight permits may be issued in accordance with §§ 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) Incorporation by Reference
PDF page 3(d) The actions shall be done in accordance with Raytheon Service Bulletin SB 32-3386, dated June 2000. 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 Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capital Street, NW., suite 700, Washington, DC.
(e) Effective Date
PDF page 3(e) This amendment becomes effective on September 10, 2001.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
Effective September 10, 2001.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 10, 2001.
AddressesPage 1
The service information referenced in this AD may be obtained from Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201-0085. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
For further information contactPage 2
Paul C. DeVore, Aerospace Engineer, Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4142; fax (316) 946-4407.
Supplementary informationPage 2
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 Raytheon Model Hawker 800XP series airplanes and certain Model Hawker 800 (U-125A military) airplanes was published in the Federal Register on May 4, 2001 (66 FR 22482). That action proposed to require a one-time inspection of an attachment bolt in the main landing gear (MLG) door system to determine whether the bolt's protruding threads have been peened; and corrective action, if necessary.
CommentsPage 2
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.
ConclusionPage 2
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
Cost impactPage 2
The FAA estimates that 115 Model Hawker 800XP series airplanes and certain Model Hawker 800 (U-125A military) airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $6,900, or $60 per airplane.
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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
Regulatory impactPage 2
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 the location provided under the caption ADDRESSES.
Adoption of the amendmentPage 2
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:
1. The authority citation for part 39 continues to read as follows:
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.
Registered aircraft · 284
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1994 | 6 |
|---|---|
| 1995 | 6 |
| 1996 | 15 |
| 1997 | 13 |
| 1998 | 21 |
| 1999 | 25 |
| 2000 | 28 |
| 2001 | 34 |
| 2002 | 35 |
| 2003 | 23 |
| 2004 | 31 |
| 2005 | 21 |
| 2006 | 5 |
| 2007 | 2 |
19 with no year recorded