| AD Number | 92-06-05 R1 | Status | Active |
| Effective Date | April 21, 1992 | Issue Date | Not specified |
| Docket Number | 91-NM-209-AD | Amendment | 39-8251 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Textron Aviation Inc. |
| Model(s) | BAe.125 Series 1000B BAe.125 Series 800A BAe.125 Series 800A (C-29A) BAe.125 Series 800A (U-125) BAe.125 Series 800B BH.125 Series 400A BH.125 Series 600A DH.125 Series 1A DH.125 Series 1A-522 DH.125 Series 1A/R-522 DH.125 Series 1A/S-522 DH.125 Series 3A DH.125 Series 3A/R DH.125 Series 3A/RA DH.125 Series 400A HS.125 Series 1B HS.125 Series 1B-522 HS.125 Series 1B/R-522 HS.125 Series 1B/S-522 HS.125 Series 3B HS.125 Series 3B/R HS.125 Series 3B/RA HS.125 Series 3B/RB HS.125 Series 3B/RC HS.125 Series 400B HS.125 Series 400B/1 HS.125 Series 401B HS.125 Series 403A(C) HS.125 Series 403B HS.125 Series 600A HS.125 Series 600B HS.125 Series 600B/1 HS.125 Series 600B/2 HS.125 Series 600B/3 HS.125 Series 700A HS.125 Series 700B HS.125 Series F3B HS.125 Series F3B/RA HS.125 Series F400B HS.125 Series F403B HS.125 Series F600B |
92-06-05 R1 BRITISH AEROSPACE: Amendment 39-8251. Revises amendment 39-8185, AD 92- 06-05. Docket No. 91-NM-209-AD.
Applicability: Model DH/BH/HS/BAe 125 series airplanes, except Model BAe 125-1000A series airplanes, certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the fuselage and subsequent decompression of the airplane, accomplish the following:
(a) Prior to the accumulation of 4,000 landings, or within 60 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with British Aerospace Service Bulletin 53-73, Revision 2, dated May 18, 1991:
(1) Perform a visual inspection of the nose landing gear (NLG) bay left and right sidewalls to detect the presence of washers or spotface under nuts.
(i) If no spotface is found, perform a visual inspection to detect damage to the web caused by nuts or washers.
(ii) Blend out any damage found, excluding cracking, prior to further flight.
(2) Perform either a dye penetrant or eddy current inspection to detect cracks on the NLG bay left and right sidewalls. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(d) The inspections shall be done in accordance with British Aerospace Service Bulletin 53- 73, Revision 2, dated May 18, 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of April 21, 1992 (57 FR 9170, March 17, 1992). 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, 1100 L Street NW., Room 8401, Washington, DC.
(e) This amendment is effective April 21, 1992.