Daily Rules, Proposed Rules, and Notices of the Federal Government
For service information identified in this proposed AD, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053-4005; telephone (972) 641-3460; fax (972) 641-3527; or at
We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive.
EASA has issued EASA AD No. 2008-0206, dated November 25, 2008, to correct the unsafe condition for the ECD Model BO 105 A, BO 105 C, BO 105 LS A-1, BO 105 D, BO 105 DS, BO 105 DB, BO 105 DBS, BO 105 DB-4, BO 105 DBS-4, BO 105 DBS-5, BO 105 S, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters, all serial numbers. The TCCA has issued Canadian AD No. CF-2009-12, dated March 24, 2009, to correct the unsafe condition for the Eurocopter Model BO 105 LS A-3 helicopters. These ADs state that during a periodical inspection, corrosion was detected on the weights in the area of the attachment thread. Since the issuance of the Canadian AD, the type certificate for the Model BO 105 LS A-3 has been transferred from Eurocopter Canada Limited to Eurocopter Deutschland (Germany).
The proposed actions are intended to detect corrosion and thread damage in the threaded area of a weight or lever, to prevent failure of a weight or lever, separation of tail rotor parts, severe vibration, and subsequent loss of control of the helicopter. You may obtain further information by examining the EASA and TCCA ADs and any related service information in the AD docket.
These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design.
Eurocopter has issued Alert Service Bulletin (ASB) No. ASB-MBB-BK 117-30-113, dated September 23, 2008, for all MBB BK 117 model “A-1 to C-1” helicopters; ASB No. ASB BO105-30-116, dated September 23, 2008, for all Model BO105 helicopters “including BO105 CB-3 and BO105 CBS-5 KLH;” and Eurocopter Canada Limited has issued ASB No. ASB BO 105 LS 30-12, dated December 12, 2008, for Model BO 105 LS A-3 helicopters. These ASBs specify visually inspecting the weights and levers to detect corrosion or mechanical damage; corrosion at an advanced stage could destroy the threads. These ASBs also specify replacing damaged weights and levers that exceed certain limits. The actions described in the mandatory EASA and TCCA ADs are intended to correct the unsafe condition, identified in these ASBs, to ensure the continued airworthiness of these helicopters.
This proposed AD would require compliance with specified portions of the manufacturer's service bulletin in conducting repetitive visual inspections of each weight and lever and would provide procedures for installing a weight or lever. Additionally, it proposes allowable tolerances for corrosion or thread damage on the threaded portion of a weight or lever and would require that a part with
This proposed AD does not provide an extra 60 flight hours or 6 months beyond the repetitive compliance time of 600 flight hours or 48 months for the repetitive inspections. These proposals only apply to those model helicopters type-certificated in the United States.
We estimate that this proposed AD would affect about 33 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. It would take approximately 4 work-hours per helicopter to remove, inspect, and install 2 lever assemblies and 4 weights per helicopter at an average labor rate of $85 per work-hour. Based on these figures, we estimate the inspection cost of this proposed AD would be $340 per helicopter or $11,220 on U.S. operators per inspection cycle. The required parts would cost about $5,332 per helicopter. We estimate the cost for replacement would be $5,672 per helicopter, assuming both lever assemblies and all 4 weights are replaced.
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in “Subtitle VII, Part A, Subpart III, Section 44701: General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.
For the reasons discussed, I certify this proposed regulation:
1. Is not a “significant regulatory action” under Executive Order 12866;
2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and
4. 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.
We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
This AD applies to Model BO-105A, BO-105C, BO-105S, and BO-105LS A-1 helicopters, with a tail rotor control lever (lever), part number (P/N) 105-317231, 105-317365, 105-31736, 105-31767, 105-31728, or 1121-31730, with tail rotor balance weight (weight) P/N 117-31715.01, 117-31715.02, 105-31728.03, 105-31732.07, or 105-31732.08; Model BO-105LS A-3 helicopters, with lever P/N 105-31736 or 105-31767, with weight P/N 117-31715.01, 117-31715.02, B642M1011 201, or 105-317171.10; and Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters, with lever P/N 117-31730, 117-317361, or 105-31736, with weight P/N 117-31714.07, 117-31715.01, 117-31720.01, or 117-31730.02, certificated in any category.
This AD defines the unsafe condition as corrosion or thread damage in the threaded area of a lever or weight. This condition could result in failure of a weight or lever, separation of a tail rotor part, severe tail rotor vibration, and subsequent loss of control of the helicopter.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
Within 100 hours time-in-service (TIS) or 2 months, whichever occurs first, and thereafter at intervals not to exceed 600 hours TIS or 48 months, whichever occurs first:
(1) Remove the weights from the lever as depicted in Figure 1 to paragraph (d) of this AD. Apply marks to the weights before they are removed in order to be able to re-establish the correct assignment and the old installation position towards the lever when the weights are installed.
(2) Visually inspect each weight and lever for corrosion and damage in the threaded areas as depicted in Figure 2 to paragraph (d) of this AD.
(i) If there is no corrosion or thread damage on either the weight or lever, before further flight, reinstall the weight by following paragraph (d)(3) of this AD.
(ii) If there is corrosion or thread damage on the threaded portion of a
(A) If the total area of corrosion or thread damage, or both, covers less than 25 percent of the length of the threaded area, the weight can be threaded (screwed) onto the lever, and the cylindrical mating surface has no damage, before further flight, remove the corrosion and reinstall the weight by following paragraph (d)(3) of this AD.
(B) If the total area of corrosion or thread damage, or both, covers 25 percent or more of the length of the threaded area, the weight cannot be threaded (screwed) onto the lever, or the cylindrical mating surface has damage, before further flight, replace the weight with an airworthy weight by following paragraph (d)(3) of this AD.
(iii) If there is corrosion or thread damage on the threaded portion of the
(A) If the thread depth does not exceed 0.3 millimeter (mm) and the diameter of the lever in the area before the threaded area is not less than 9.95 mm after polish out, before further flight, install airworthy weights to the lever by following paragraph (d)(3) of this AD.
(B) If the thread depth is 0.3 mm or greater or the diameter of the lever in the area before the threaded area is less than 9.95 mm after polish out, before further flight, replace the lever with an airworthy lever.
(3) Apply corrosion preventive paste onto the thread of the lever and install weights to
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; email
(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
The subject of this AD is addressed in the European Aviation Safety Agency (Germany) AD No. 2008-0206, dated November 25, 2008, and in the Transport Canada Civil Aviation AD No. CF-2009-12, dated March 24, 2009.
Joint Aircraft Service Component (JASC) Code: 6420, Tail Rotor Head.