Airworthiness directives: Bell,
[Federal Register: August 31, 1999 (Volume 64, Number 168)]
[Rules and Regulations]
[Page 47362-47365]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31au99-5]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-72-AD; Amendment 39-11268; AD 99-18-02]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model 205A-1 and 205B Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 205A-1 and 205B helicopters, that requires inspecting the vertical fin spar cap (spar cap) for cracking, corrosion, or disbonding; modifying the vertical fin; and replacing the left-hand spar cap. This amendment is prompted by five accidents involving helicopters of similar type design. The actions specified by this AD are intended to detect fatigue cracking or corrosion on the spar cap, which could lead to failure of the vertical fin spar, loss of the tail rotor, and subsequent loss of control of the helicopter.
DATES: Effective October 5, 1999.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 5, 1999.
ADDRESSES: The service information referenced in this AD may be obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280-3391, fax (817) 280-6466. This information may be examined 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.
FOR FURTHER INFORMATION CONTACT: Mike Kohner, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5447, fax (817) 222-5783.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to BHTI Model 205A-1 and 205B helicopters was published in the Federal Register on June 3, 1999 (64 FR 29814). That action proposed to require:
--Visually inspecting the spar cap for any crack or disbonding; --Inspecting the spar cap for any disbonding using a tap hammer; --Modifying the vertical fin; --After modifying the vertical fin, inspecting the spar cap for any cracks using a dye-penetrant inspection method; and --Replacing the left-hand spar cap.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial changes. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.
The FAA estimates that 150 helicopters of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per helicopter to accomplish the initial inspections, 0.5 work hour for the repetitive inspections, and 180 hours to replace the vertical fin spar assembly, and that the average labor rate is $60 per work hour. Required parts will cost approximately $300 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $1,705,500 to conduct the initial inspection and one repetitive inspection, and replace the vertical vin spar assembly on all the fleet.
The regulations adopted herein will not have substantial direct effects 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. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is not a ``significant regulatory action'' under
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Executive Order 12866; (2) is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended].
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Section 39.13 is amended by adding a new airworthiness directive to read as follows:
AD 99-18-02-AD Bell Helicopter, Textron, Inc.: Amendment 39-11268. Docket No. 98-SW-72-AD.
Applicability: Model 205A-1 helicopters with vertical fin spar cap, part number (P/N) 212-030-447-001 or -101, installed, and Model 205B helicopters with vertical fin spar cap, P/N 212-030-447-101, installed, 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 (d) 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 failure of the vertical fin (fin) spar, loss of the tail rotor, and subsequent loss of control of the helicopter, accomplish the following:
(a) For Model 205A-1 helicopters with a fin spar cap (spar cap), P/N 212-030-447-001, installed, accomplish the following:
(1) Within 8 hours time-in-service (TIS), modify the vertical fin and visually inspect the fin spar for cracks in accordance with Part I (A1), paragraphs 1 through 4 of Bell Helicopter Textron, Inc. Alert Service Bulletin No. 205-98-70, Revision A, dated September 21, 1998 (ASB).
(i) If a crack is discovered on the fin spar, replace the fin spar assembly with an airworthy fin spar assembly before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(ii) After inspecting, apply MIL-PRF-81352 clear lacquer or an equivalent coating to the area where the paint and primer were removed. Spray, brush, or wipe on a protective coat of MIL-C-16173, Grade 2, or equivalent compound, over the clear lacquer or equivalent coating.
(iii) Install the inspection door, intermediate gearbox cover, and tail rotor driveshaft cover.
(2) After initially modifying and inspecting the fin, inspect the fin spar for cracks at intervals not to exceed 8 hours TIS as follows:
(i) Accomplish Part I (A2), paragraphs 1 through 3, of the ASB.
(ii) If a crack is discovered on the fin spar, replace the fin spar cap or spar assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(iii) After inspecting, accomplish Part I (A2), paragraphs 5 and 6, of the ASB.
(3) Within 25 hours TIS, inspect and modify the fin assembly as follows:
(i) Accomplish Part II (C1), paragraph 1, of the ASB.
(ii) Remove the clip, part number (P/N) 212-030-099-091, and radius block, P/N 212-030-099-095, if existing. Remove the retainer, P/N 212-030-121-037, and sufficient rivets from the bottom row of the forward left-hand fin skin to allow trimming of the forward left-hand skin along the skin ``cutline'', approximately fin station 66.31 (see Figure 2 of the ASB).
(iii) Before drilling or reaming, inspect all holes in the spar cap where rivets were removed for short edge distance. If an existing edge distance will be less than 1.5 times the diameter of the drill or reamed hole, repairs must be performed and must be FAA approved before proceeding.
(iv) Accomplish Part II (C1), paragraphs 3, 4, and 6, in the ASB.
(v) If a crack is discovered on the fin spar, replace the fin spar cap or spar assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(vi) Accomplish Part II (C1), paragraphs 10 through 14, of the ASB.
(4) After initially modifying and dye-penetrant inspecting the fin spar, inspect the fin spar at intervals not to exceed 300 hours TIS as follows:
(i) Accomplish Part II (C2), paragraphs 1, 2, 3, 4, 5, and 7, of the ASB.
(ii) If a crack is discovered on the fin spar, replace the fin spar cap or spar assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(iii) Accomplish Part II (C2), paragraphs 11 through 14, of the ASB.
(5) Within 12 calendar months, remove the left-hand fin spar cap, P/N 212-030-447-001. Replace it with an airworthy fin spar cap or spar assembly configuration that has been demonstrated to the FAA to satisfy the structural fatigue requirements of repeated high- torque events and is approved by the Manager, Rotorcraft Standards Staff.
(6) Installation of a fin spar cap or assembly that has been approved by the Manager, Rotorcraft Standards Staff, constitutes terminating action for the requirements of this AD.
(b) For Model 205A-1 helicopters with a fin spar cap, P/N 212- 030-447-101, installed, accomplish the following:
(1) Within 8 hours TIS, modify the vertical fin and visually inspect the fin spar for cracks in accordance with Part II (A1), paragraphs 1 through 5, of the ASB.
(i) If a crack is discovered on the fin spar, replace the fin spar cap or assembly with an airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(ii) After inspecting, apply MIL-PRF-81352 clear lacquer or an equivalent coating to the two lower rivet holes and on the surface where paint and primer were removed. Spray, brush, or wipe on a protective coat of MIL-C-16173, Grade 2 or equivalent compound, over the clear lacquer or equivalent coating. To facilitate subsequent inspections, do not replace the two lower rivets (see Figure 2 of the ASB).
(iii) Before drilling or reaming, inspect all holes in the spar cap where rivets were removed for short edge distance. If an existing edge distance will be less than 1.5 times the diameter of the drill or reamed hole, repairs must be performed and must be FAA approved before proceeding.
(iv) Fasten the forward left-hand fin skin and the retainer, P/N 212-030-121-037, to the spar assembly using Hi-Loks and blind rivets as specified in Figure 2 of the ASB. Reinstall the clip and radius block, if existing, that were removed in accordance with paragraph 2 of Part II (A1) of the ASB.
(v) Refinish the reworked area.
(vi) Install the inspection door, intermediate gearbox cover, and tail rotor driveshaft cover.
(2) After initially modifying and inspecting the fin, inspect the fin spar for cracks at intervals not to exceed 8 hours TIS as follows:
(i) Accomplish Part II (A2), paragraphs 1 through 3, of the ASB.
(ii) If a crack is discovered on the fin spar, replace the fin spar cap or assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(iii) After inspecting, accomplish Part II (A2), paragraphs 5 and 6, of the ASB.
(3) Within 25 hours TIS, modify and inspect the vertical fin as follows:
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(i) Accomplish Part II (C1), paragraph 1, of the ASB.
(ii) Remove the clip, P/N 212-030-099-091, and radius block, P/N 212-030-099-095, if existing. Remove the retainer, P/N 212-030-121- 037, and sufficient rivets from the bottom row of the forward left- hand fin skin to allow trimming of the forward left-hand fin skin along the skin ``cutline'', approximately fin station 66.31 (see Figure 2 of the ASB).
(iii) Before drilling or reaming, inspect all holes in the spar cap where rivets were removed for short edge distance. If an existing edge distance will be less than 1.5 times the diameter of the drill or reamed hole, repairs must be performed and must be FAA approved before proceeding.
(iv) Accomplish Part II (C1), paragraphs 3, 4, and 6, of the ASB.
(v) If a crack is discovered on the fin spar, replace the fin spar cap or assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(vi) Accomplish Part II (C1), paragraphs 10 through 14, of the ASB.
(4) After initially modifying and dye-penetrant inspecting the fin spar, inspect the fin spar at intervals not to exceed 300 hours TIS as follows:
(i) Accomplish Part II (C2), paragraphs 1 through 7, of the ASB.
(ii) If a crack is discovered on the fin spar, replace the fin spar cap or assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(iii) Accomplish Part II (C2), paragraphs 11 through 14, of the ASB.
(5) Within 25 hours TIS, and thereafter at intervals not to exceed 300 hours TIS, inspect the fin spar as follows:
(i) Accomplish Part II (B), paragraphs 1 through 13, of the ASB.
(ii) Repair any disbonding discovered during the inspection before further flight.
(6) Within 12 calendar months, remove the left-hand fin spar cap, P/N 212-030-447-101. Replace it with an airworthy fin spar cap or spar assembly configuration that has been demonstrated to the FAA to satisfy the structural fatigue requirements of repeated high- torque events and is approved by the Manager, Rotorcraft Standards Staff.
(7) Installation of a fin spar that has been approved by the Manager, Rotorcraft Standards Staff, that satisfies the requirements of paragraph (b)(6) of this AD constitutes terminating action for the requirements of this AD.
(c) For Model 205B helicopters with a fin spar cap, P/N 212-030- 447-101, installed, accomplish the following:
(1) Within 8 hours TIS, modify the fin and visually inspect the fin spar for cracks in accordance with Part I (A1), paragraphs 1 through 5, of Bell Helicopter Textron, Inc. Alert Service Bulletin No. 205B-98-26, Revision A, dated September 21, 1998 (205B ASB).
(i) If a crack is discovered on the fin spar, replace the fin spar cap or assembly with airworthy parts before further flight. Repair any corrosion or disbonding discovered during the inspection before further flight.
(ii) After inspecting, apply MIL-PRF-81352 clear lacquer or an equivalent coating to the two lower rivet holes and on the surface where paint and primer were removed. Spray, brush, or wipe on a protective coat of MIL-C-16173, Grade 2, or equivalent compound, over the clear lacquer. To facilitate subsequent inspections, do not replace the two lower rivets (see Figure 2 of the 205B ASB).
(iii) Before drilling or reaming, inspect all holes in the spar cap where rivets were removed for short edge distance. If an existing edge distance will be less than 1.5 times the diameter of the drill or reamed hole, repairs must be performed and must be FAA approved before proceeding.
(iv) Fasten the forward left-hand fin skin and the retainer, P/N 212-030-121-037, to the spar assembly using Hi-Loks and blind rivets as specified in Figure 2 of the 205B ASB. Reinstall the clip and radius block, if existing, removed in paragraph 2 of Part I (A1) of the 205B ASB.
(v) Install the inspection door, intermediate gearbox cover, and tail rotor driveshaft cover.
(2) After initially modifying and inspecting the fin, inspect the fin spar for cracks at intervals not to exceed 8 hours TIS as follows:
(i) Accomplish Part I (A2), paragraphs 1 through 3, of the 205B ASB.
(ii) If a crack is discovered on the spar, replace the fin spar cap or assembly with airworthy parts before further flight. Any corrosion or disbonding discovered during the inspection must be repaired before further flight.
(iii) After inspecting, accomplish Part I (A2), paragraphs 5 and 6, of the 205B ASB.
(3) Within 25 hours TIS, modify and inspect the fin as follows:
(i) Accomplish Part I (C1), paragraph 1 of the 205B ASB.
(ii) Remove the clip, P/N 212-030-099-091, and radius block, P/N 212-030-099-095, if existing. Remove the retainer, P/N 212-030-121- 037, and sufficient rivets from the bottom row of the forward left- hand fin skin to allow trimming of the forward left-hand fin skin along the skin ``cutline'', approximately fin station 66.31 (see Figure 2 of the 205B ASB).
(iii) Before drilling or reaming, inspect all holes in the spar cap where rivets were removed for short edge distance. If an existing edge distance will be less than 1.5 times the diameter of the drill or reamed hole, repairs must be performed and must be FAA approved before proceeding.
(iv) Accomplish Part I (C1), paragraphs 3, 4, and 6, in the 205B ASB.
(v) If a crack is discovered on the spar, replace the fin spar cap or assembly with airworthy parts before further flight. Any corrosion or disbonding discovered during the inspection must be repaired before further flight.
(vi) Accomplish Part I (C1), paragraphs 10 through 14, of the 205B ASB.
(4) After initially modifying and dye-penetrant inspecting the fin spar, inspect the fin spar at intervals not to exceed 300 hours TIS as follows:
(i) Accomplish Part I (C2), paragraphs 1, 2, 3, 4, 5, and 7, of the 205B ASB.
(ii) If a crack is discovered on the spar, replace the fin spar cap or assembly with airworthy parts before further flight. Any corrosion or disbonding discovered during the inspection must be repaired before further flight.
(iii) Accomplish Part I (C2), paragraphs 11 through 14, of the 205B ASB.
(5) Within 25 hours TIS, inspect the fin spar at intervals not to exceed 300 hours TIS as follows:
(i) Accomplish Part I (B), paragraphs 1 through 13, of the 205B ASB.
(ii) Any disbonding discovered during the inspection must be repaired before further flight.
(6) Within 12 calendar months, remove the left-hand fin spar cap, P/N 212-030-447-101. Replace it with an airworthy fin spar cap configuration that has been demonstrated to the FAA to satisfy the structural fatigue requirements of repeated high-torque events and is approved by the Manager, Rotorcraft Standards Staff.
(7) Installation of a fin spar that satisfies the above requirements and has been approved by the Manager, Rotorcraft Standards Staff, constitutes a terminating action for the requirements of this AD.
(d) 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, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through a FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff.
Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.
(e) 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.
(f) The modification of the vertical fin, the visual and dye- penetrant inspections, and any necessary repairs shall be done in accordance with Bell Helicopter Textron, Inc. Alert Service Bulletin No. 205-98-70, Revision A, or No. 205B-98-26, Revision A, both dated September 21, 1998, as applicable. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280-3391, fax (817) 280-6466. 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.
(g) This amendment becomes effective on October 5, 1999.
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Issued in Fort Worth, Texas, on August 18, 1999. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-22077Filed8-30-99; 8:45 am]
BILLING CODE 4910-13-U
