AD 2014-12-04 Airworthiness Directives; Bell Helicopter Textron, Inc. (BHTI) Helicopters

This AD supersedes AD 2003-01-04, Amendment 39-13015 (68 FR 1955, January 15, 2003).

(1) Within 10 hours time-in-service (TIS), create a component history card or equivalent record and determine and record the total hours TIS for each grip. If the total hours TIS cannot be determined from the helicopter records, assume and record 50 hours TIS for each month for which the hours cannot be determined. Continue to count and record the hours TIS and begin to count and record the number of times the helicopter engine(s) are started (engine start/stop cycles). (2) Within 10 hours TIS, and thereafter at intervals not to exceed 25 hours TIS, without removing the main rotor blades: (i) Clean the exposed surfaces of the upper and lower tangs of each grip with denatured alcohol, and wipe dry. (ii) Using a 10-power or higher magnifying glass, visually inspect the exposed surfaces of the upper and lower tangs of each grip for a crack. Pay particular attention to the lower surface of each lower grip tang from the main rotor blade bolt-bushing flange to the leading and trailing edge of each grip tang as depicted in Figure 1 to Paragraphs (f)(2)(ii) and (f)(4)(ii) of this AD. ER19JN14.000 (3) At the intervals shown in Table 2 to Paragraph (f)(3) of this AD, ultrasonic (UT) inspect each grip in accordance with the Bell Helicopter Textron Nondestructive Inspection Procedure, Log No. 00-340, Revision E, dated April 9, 2002. The UT inspection of the grip must be performed by a Non-Destructive Testing (NDT) UT Level I Special, Level II, or Level III inspector who is qualified under the guidelines established by MIL-STD-410E, ATA Specification 105, AIA-NAS-410, or an FAA-accepted equivalent for qualification standards of NDT Inspection/Evaluation Personnel. Table 2 to Paragraph ( f )(3)—Ultrasonic Inspection Intervals UT inspect grip, P/N: Within 30 days, or the following hours TIS for the grip, whichever occurs later: Thereafter, at intervals not to exceed the following hours TIS or engine start/stop cycles, whichever occurs first: Hours TIS Engine start/stop cycles 204-011-121-009 or ASI-4011-121-9 4,000 400 1,600 204-011-121-121 500 150 600 204-011-121-005 or -113, if the grip was EVER installed on a Model 205B helicopter 4,000 400 1,600 204-011-121-117, if the grip was NEVER installed on a Model 205B helicopter 4,000 150 600 204-011-121-117, if the grip was EVER installed on a Model 205B helicopter 500 150 600 Note 1 to Paragraph (f)(3) of this AD: You can find the Nondestructive Inspection Procedure attached to BHTI Alert Service Bulletin (ASB) No. 205B-02-39, Revision B, dated November 22, 2002, or BHTI ASB No. 212 02-116, Revision A, dated October 30, 2002. (4) At intervals not to exceed 1,200 hours TIS or 24 months, whichever occurs first: (i) Remove each main rotor blade, and (ii) Inspect each grip buffer pad on the inner surfaces of each grip tang for delamination as depicted in Figure 1 to Paragraphs (f)(2)(ii) and (f)(4)(ii) of this AD. If there is any delamination, remove the buffer pad and inspect the grip surface for corrosion or other damage. Note 2 to Paragraph (f)(4) of this AD: This inspection interval coincides with the main rotor tension-torsion strap replacement times. (5) Within 2,400 hours TIS, or at the next overhaul of the main rotor hub, whichever occurs first, and thereafter at intervals not to exceed 2,400 hours TIS: (i) Remove each main rotor blade. (ii) Remove each grip buffer pad (if installed) from the inner surfaces of each grip tang. (iii) Visually inspect the grip tang surfaces for corrosion or other damage. (iv) Fluorescent-penetrant inspect the grip for a crack, paying particular attention to the upper and lower grip tangs. When inspecting any grip, P/N 204-011-121-005, -009, -113, or ASI-4011-121-9, pay particular attention to the leading and trailing edges of the grip barrel. (6) Before further flight: (i) Replace any cracked grip with an airworthy grip. (ii) Replace any grip with any corrosion or other damage with an airworthy grip, or repair the grip if the corrosion or other damage is within maximum repair damage limitations. (iii) Replace any grip, P/N 204-011-121-009 or ASI-4011-121-9, which has been in service for 15,000 or more hours TIS. (iv) Replace any grip, P/N 204-011-121-121, which has been in service for 25,000 or more hours TIS. (7) Revise the Airworthiness Limitations sections of the applicable maintenance manuals or the Instructions for Continued Airworthiness (ICAs) by establishing a new retirement life of 15,000 hours TIS for grip P/N 204-011-121-009 or ASI-4011-121-9, and 25,000 hours TIS for grip P/N 204-011-121-121, by making pen and ink changes or inserting a copy of this AD into the applicable maintenance manual or ICAs. (8) Record a 15,000 hours TIS life limit for each grip P/N 204-011-121-009 or ASI-4011-121-9, and a 25,000 hours TIS life limit for each grip P/N 204-011-121-121, on the applicable component history card or equivalent record.

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170, fax (817) 222-5783, email mike.kohner@faa.gov or 7-avs-asw-170@faa.gov . (2) For operations conducted under a Part 119 operating certificate or under 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.

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.

This AD defines the unsafe condition as a crack in the main rotor grip (grip), which could result in failure of a grip, separation of a main rotor blade, and subsequent loss of control of the helicopter.