Airworthiness Directive · Amendment 39-15101 · MD Helicopters, Inc. Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A Helicopters
MD Helicopters, Inc. Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A Helicopters
Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A helicopters, with any of the components listed in the Applicability Table installed, excluding any helicopter with Aerometals strut (part number (P/N) 369XH6001-41, -42, -51, or -52) installed in accordance with Supplemental Type Certificate (STC) No. SR00981LA, certificated in any category:
| Component name | Component part No. (P/N) |
|---|---|
| Mid Aft Fairing Assembly | 369H6200-61, -62, standard gear. |
| Aft Support Assembly | 369H6200-23, -24 (-23 to be reinstalled on the right-hand side and -24 to be reinstalled on the left-hand side, all configurations). |
| Aft Fairing Assembly | 369H92113-91, -92, extended gear. |
| Aft Filler Assembly | 369H92113-131, -132, extended gear. |
| Aft Fillet Assembly | 369A6200-45, -46, standard gear. |
| Aft Fillet Assembly | 369H92113-111, -112, extended gear. |
| Mid Fwd Fairing Assembly | 369H6200-41, -42, standard gear. |
| Fwd Fairing Assembly | 369H92113-81, -82, extended gear. |
| Fwd Support Assembly | 369H6200-23, -24 (-23 becomes right-hand side and -24 becomes left-hand side). |
| Fwd Filler Assembly | 369H92113-121, -122, extended gear. |
| Fwd Fillet Assembly | 369A6200-57, -58, standard gear. |
| Fwd Fillet Assembly | 369H92113-101, -102, extended gear. |
This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A helicopters that requires inspecting each landing gear fairing support assembly (support assembly), replacing or reworking certain forward and aft landing gear assemblies, and creating an access hole to facilitate inspections and a recurring inspection. A terminating action for the requirements of this AD is also provided. This amendment is prompted by five reports of landing gear strut (strut) failures. The actions specified by this AD are intended to detect a crack that could result in the failure of a strut and subsequent loss of control of the helicopter during landing.
Required as indicated.
To detect a crack that could result in the failure of a strut and subsequent loss of control of the helicopter during landing, accomplish the following:
(a) Within 4 months, unless accomplished previously, remove all landing gear fairings (fairings) and inspect each landing gear fairing support assembly (support assembly) to determine the number and location of the rivets attaching the support assembly to the landing gear strut assembly (strut assembly).
(1) If three rivets (forward, aft and inboard) are used to attach the support assembly to the strut assembly,
(i) For each FORWARD landing gear assembly, remove the landing gear fillet assembly (fillet assembly), the three rivets, and the support assembly, and clean and dye-penetrant inspect the area in and around the 0.125 (3.18mm) diameter hole in the inboard surface of the strut assembly.
(A) If the strut assembly is cracked, replace the cracked strut assembly with an airworthy strut assembly and install the other landing gear components in accordance with steps (6) through (11) of paragraph C of the Accomplishment Instructions of MD Helicopters Service Bulletin SB369H-244, SB369E-094, SB500N-022, SB369D-200, and SB369F-078, dated April 7, 2000 (SB).
(B) If the strut assembly is not cracked, rework the landing gear assembly and install the other landing gear components in accordance with steps (5) through (11) of paragraph C of the Accomplishment Instructions of the SB.
(ii) For each AFT landing gear assembly, remove the fillet assembly, the three rivets, and the support assembly, and clean and dye-penetrant inspect the area in and around the 0.125 (3.18mm) diameter hole in the inboard surface of the strut assembly.
(A) If the strut assembly is cracked, replace the cracked strut assembly with an airworthy strut assembly and install the other landing gear components in accordance with steps (6) through (13) of paragraph B of the Accomplishment Instructions of the SB.
(B) If the strut assembly is not cracked, rework the landing gear assembly and install the other landing gear components in accordance with steps (5) through (13) of Paragraph B of the Accomplishment Instructions of the SB.
(2) If only two rivets (forward and aft) are used to attach the support assembly to the strut assembly and a third rivet hole has not been drilled in the strut, neither the inspection of the strut assembly nor the rework of those landing gear assemblies is required by this AD.
(b) At intervals not to exceed 100 hours TIS or during each annual inspection, whichever occurs first, for any strut assembly that has a third rivet hole, remove the fairing inspection button plug and clean and inspect the area in and around the rivet hole for cracks using a bright light and a 10x or higher magnifying glass.
(1) If any FORWARD strut assembly is cracked, replace the cracked strut with an airworthy strut assembly.
(2) If any AFT strut assembly is cracked, replace the cracked strut with an airworthy strut assembly.
(c) Installing a strut assembly that has only 2 rivet holes is terminating action for the requirements of this AD.
Note 1: For the Model 369D, 369E, 369F, 369FF, and 500N helicopters, the Handbook of Maintenance Instruction, Servicing and Maintenance, HMI, CSP-HMI-2, Chapter 32, Section 32-10-00, “Landing Gear Strut Inspection” pertains to the subject of this AD.
Note 2: For the Model 369A (OH-6A), 369H, 369HE, 369HS, and 369HM helicopters, the Basic Handbook of Maintenance Instructions CSP-H-2, Section 6, “Landing Gear” pertains to the subject of this AD.
(d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: John Cecil, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-5228, fax (562) 627-5210 for information about previously approved alternative methods of compliance.
(e) The replacements and installations shall be done in accordance with the specified portions of MD Helicopters Service Bulletin SB369H-244, SB369E-094, SB500N-022, SB369D-200, and SB369F-078, dated April 7, 2000. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-800-388-3378, fax 480-346-6813, or on the Web at http://www.mdhelicopters.com. 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_locations.html.
(f) This amendment becomes effective on July 19, 2007.
