Airworthiness directives › 99-22-01
AD 99-22-01 Airworthiness Directives; Eurocopter Deutschland GmbH Model EC135 P1 and T1 Helicopters
Models named: EC135 P1, T1. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model EC135 P1 and T1 helicopters, serial numbers 0005 through 0120, inclusive, 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 (c) 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 fracture of the bearing connecting frame flange (frame flange), failure of the tail rotor drive shaft, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, conduct a dye-penetrant inspection of the tail boom frame flange at the attachment points of the tail rotor drive shaft bearing (see location I in Figure 1 in Eurocopter Deutschland GmbH (ECD) Alert Service Bulletin (ASB) EC 135-53A-010, Revision 2, dated July 22, 1999) in accordance with the Accomplishment Instructions, paragraph 3.A., of ASB EC 135-53A-010, Revision 2, dated July 22, 1999, and Figure 1 of ASB 135-53A-009, dated March 23, 1999. If a crack is found, replace the unairworthy frame flange with an airworthy frame flange. Thereafter, conduct the dye-penetrant inspection at intervals not to exceed 15 hours time- in-service (TIS) until the requirements in paragraph (b) of this AD are accomplished. (b) Within 7 days, install an additional bearing support bracket on the frame flange in accordance with the Accomplishment Instructions, paragraph 3.B., of ASB EC 135-53A-010, Revision 2 dated July 22, 1999. Thereafter, at intervals not to exceed 50 hours TIS, inspect for a crack or for misalignment of the slippage marks on the frame flange. (c) 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 this AD, if any, may be obtained from the Regulations Group, Rotorcraft Directorate. (d) 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. (e) The dye-penetrant inspections shall be done in accordance with the Accomplishment Instructions, paragraph 3.A., of Eurocopter Deutschland GmbH Alert Service Bulletin EC 135-53A-010, Revision 2, dated July 22, 1999, and Figure 1 of Eurocopter Deutschland GmbH Alert Service Bulletin 135-53A-009, dated March 23, 1999. The modification shall be done in accordance with the Accomplishment Instructions, paragraph 3.B., of Eurocopter Deutschland GmbH Alert Service Bulletin EC 135-53A-010, Revision 2, dated July 22, 1999. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. 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. (f) This amendment becomes effective on December 17, 1999, to all persons except those persons to whom it was made immediately effective by Emergency Priority Letter AD 99-22-01, issued October 12, 1999, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on November 17, 1999. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-30623 Filed 12-1-99; 8:45 am] BILLING CODE 4910-13-P
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1