[Federal Register Volume 64, Number 155 (Thursday, August 12, 1999)]
[Rules and Regulations]
[Pages 43905-43907]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20754]
[[Page 43905]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-73-AD; Amendment 39-11252; AD 99-17-03]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
204B, 205A, and 205A-1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 204B,
205A, and 205A-1 helicopters, that currently requires modifying and
inspecting the vertical fin spar (fin spar) for cracks. This amendment
requires modification and visual and dye-penetrant inspections of the
fin spar for cracks, and if a crack is discovered, replacing the fin
spar. A tapping test for disbonding and replacing certain fin spars
within 12 calendar months is also required. This amendment is prompted
by an accident involving a Model 205A-1 helicopter and four other
accidents involving helicopters of similar type design. The actions
specified by this AD are intended to prevent failure of the fin spar,
loss of the tail rotor, and subsequent loss of control of the
helicopter.
DATES: Effective September 16, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 16, 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: Harry Edmiston, Aerospace Engineer,
Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5158, fax
(817) 222-5783.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 97-18-11,
Amendment 39-10520 (63 FR 26429), applicable to BHTI Model 204B, 205A,
and 205A-1 helicopters, was published in the Federal Register on May
26, 1999 (64 FR 28420). That action proposed to require initial and
repetitive inspections of the fin spar for cracks. Also proposed was a
requirement to replace the fin spar within 12 calendar months.
Replacing the fin spar with a FAA-approved fin spar configuration that
satisfies the structural fatigue requirement of repeated high torque
events would constitute a terminating action for the requirements of
the AD. That action was prompted by an accident involving a Model 205A-
1 helicopter and four other accidents involving helicopters of similar
type design.
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.
The FAA estimates that 150 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 8 work hours per
helicopter to accomplish the initial inspection and 0.5 work hour to
accomplish each repetitive inspection. Replacing the fin spar will take
approximately 150 work hours. The average labor rate is $60 per work
hour. The manufacturer has stated that parts will be provided at no
cost. Based on these figures, the total cost impact of the proposed AD
on U.S. operators is estimated to be $76,500 for the initial inspection
and one repetitive inspection, and $1,350,000 to replace the fin spars
on the entire 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 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
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-10520 (63 FR
26429, May 13, 1998), and by adding a new airworthiness directive (AD),
Amendment 39-11252, to read as follows:
AD 99-17-03 Bell Helicopter Textron, Inc.: Amendment 39-11252.
Docket No. 98-SW-73-AD. Supersedes AD 97-18-11, Amendment 39-10520,
Docket No. 97-SW-32-AD.
Applicability: Model 204B helicopters with vertical fin spar
(fin spar), part number (P/N) 205-030-899-001, -089, P/N 205-030-
846-001, -003, -047, -049, or P/N 204-030-825-063, -065, installed,
and Model 205A and 205A-1 helicopters, with fin spar, P/N 205-030-
899-101, P/N 205-030-846-087, -089, or P/N 205-032-851-003, -007, -
009, 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 (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 failure of the fin spar, loss of the tail rotor, and
subsequent loss of control of the helicopter, accomplish the
following:
[[Page 43906]]
(a) For Model 204B helicopters:
(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 5 of Bell Helicopter Textron
(BHTI) Alert Service Bulletin (ASB) 204B-98-50, dated October 22,
1998.
(i) If a crack is discovered on the 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 inspection, apply MIL-PRF-81352 TYI clear lacquer or
equivalent to the inside of 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, over
the clear lacquer. To facilitate subsequent inspections, do not
replace the two lower rivets. See Figure 2 of BHTI ASB 204B-98-50,
dated October 22, 1998.
Note 2: BHTI-MED-SRM-1, pages 3-36 through 3-38, pertain to the
installation of Hi-Loks.
(iii) Before drilling or reaming, inspect all holes in the spar
cap where rivets were removed for short edge distance. An existing
edge distance less than 1.5 times the diameter of the drill or
reamed hole must have FAA approval of the reworked area before
proceeding.
(iv) Fasten the forward left-hand fin skin to the spar assembly
using Hi-Loks and blind rivets as specified in Figure 2 of BHTI ASB
204B-98-50, dated October 22, 1998.
(v) Refinish the reworked area.
(2) After initial modification and inspection of the fin,
thereafter 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 BHTI ASB
204B-98-50, dated October 22, 1998.
(ii) If a crack is discovered on the 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.
(iii) After inspection, accomplish Part I (A2), paragraphs 5 and
6 of BHTI ASB 204B-98-50, dated October 22, 1998.
(3) Within 25 hours TIS, modify and inspect the vertical fin as
follows:
(i) Accomplish Part I (C1), paragraph 1 of BHTI ASB 204B-98-50,
dated October 22, 1998.
(ii) Remove 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 64.31
(see Figure 2 of BHTI ASB 204B-98-50, dated October 22, 1998).
(iii) Before drilling or reaming, inspect all holes in the spar
cap where rivets were removed for short edge distance. An existing
edge distance less than 1.5 times the diameter of the drill or
reamed hole must have FAA approval of the reworked area before
proceeding.
(iv) Accomplish Part I (C1), paragraphs 3, 4, and 6 of BHTI ASB
204B-98-50, dated October 22, 1998.
(v) If a crack is discovered on the 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.
(vi) Accomplish Part I (C1), paragraphs 10 through 14 of BHTI
ASB 204B-98-50, dated October 22, 1998.
(4) After the initial modification and dye-penetrant inspection
of the fin spar, thereafter at intervals not to exceed 300 hours
TIS, inspect the fin spar as follows:
(i) Accomplish Part I (C2), paragraphs 1, 2, 3, 4, 5, and 7 of
BHTI ASB 204B-98-50, dated October 22, 1998.
(ii) If a crack is discovered on the 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.
(iii) Accomplish Part I (C2), paragraphs 11 through 14 of BHTI
ASB 204B-98-50, dated October 22, 1998.
(5) Within 25 hours TIS, and thereafter at intervals not to
exceed 300 hours TIS, inspect the fin spar as follows:
(i) Accomplish Part I (B), paragraphs 1 through 13 of BHTI ASB
204B-98-50, dated October 22, 1998.
(ii) Repair any disbonding discovered during the inspection
before further flight.
(6) Within 12 calendar months, remove fin spar P/N 205-030-899-
001, or -089, or P/N 205-030-846-001, -003, -047, or -049, or P/N
204-030-825-063, or -065. Replace it with an airworthy fin spar
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 replacement fin spar approved by the
Manger, Rotorcraft Standards Staff, constitutes a terminating action
for the requirements of this AD.
(b) For Model 205A and 205A-1 helicopters:
(1) Within 8 hours TIS, modify the vertical fin and visually
inspect the fin spar for cracks in accordance with Part I (A1),
paragraphs 1 through 5 of BHTI ASB 205-98-71, Revision A, dated
September 21, 1998.
(i) If a crack is discovered on the 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 inspection, apply MIL-PRF-81352 TYI clear lacquer or
equivalent to the inside of 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, over
the clear lacquer. To facilitate subsequent inspections do not
replace the two lower rivets. See figure 2 of BHTI ASB 205-98-71,
Revision A, dated September 21, 1998.
(iii) Before drilling or reaming, inspect all holes in the spar
cap where rivets were removed for short edge distance. An existing
edge distance less than 1.5 times the diameter of the drill or
reamed hole must have FAA approval of the reworked area before
proceeding.
(iv) Fasten the forward left-hand fin skin and the retainer, P/N
205-032-851-045, to the fin spar assembly using Hi-Loks and blind
rivets as specified in Figure 2 of BHTI ASB 205-98-71, Revision A,
dated September 21, 1998. Reinstall clip and radius block (if
existing) removed in paragraph 2 of Part 1 (A1) of BHTI ASB 205-98-
71, Revision A, dated September 21, 1998.
(v) Refinish the reworked area.
(2) After initial modification and inspection of the vertical
fin, thereafter, 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 BHTI ASB
205-98-71, Revision A, dated September 21, 1998.
(ii) If a crack is discovered on the 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.
(iii) After inspection, accomplish Part I (A2), paragraphs 5 and
6, of BHTI ASB 205-98-71, Revision A, dated September 21, 1998.
(3) Within 25 hours TIS, modify and inspect the vertical fin as
follows:
(i) Accomplish Part I (C1), paragraph 1 of BHTI ASB 205-98-71,
Revision A, dated September 21, 1998.
(ii) Remove the clip, P/N 212-030-099-091, and radius block, P/N
212-030-099-095, if present. Remove the retainer, P/N 205-032-851-
045, 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'', at approximately Fin Station 66.31 (see
Figure 2 of BHTI ASB 205-98-71, Revision A, dated September 21,
1998).
(iii) Before drilling or reaming, inspect all holes in the spar
cap where rivets were removed for short edge distance. An existing
edge distance less than 1.5 times the diameter of the drill or
reamed hole must have FAA approval of the reworked area before
proceeding.
(iv) Accomplish Part I (C1), paragraphs 3, 4, and 6 in BHTI ASB
205-98-71, Revision A, dated September 21, 1998.
(v) If a crack is discovered on the 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.
(vi) Accomplish Part I (C1) paragraphs 10 through 14 of BHTI ASB
205-98-71, Revision A, dated September 21, 1998.
(4) After the initial modification and dye-penetrant inspection
of the fin spar, thereafter, at intervals not to exceed 300 hours
TIS, inspect the fin spar as follows:
(i) Accomplish Part I (C2), paragraphs 1, 2, 3, 4, 5, and 7 of
BHTI ASB 205-98-71, Revision A, dated September 21, 1998.
(ii) If a crack is discovered on the spar, replace the fin spar
assembly with an airworthy fin spar assembly before further flight.
Repair any corrosion or disbonding
[[Page 43907]]
discovered during the inspection before further flight.
(iii) Accomplish Part I (C2), paragraphs 11 through 14 of ASB
205-98-71, Revision A, dated September 21, 1998.
(5) Within 25 hours TIS, and thereafter at intervals not to
exceed 300 hours TIS inspect the fin spar as follows:
(i) Accomplish Part I (B), paragraphs 1 through 13 of BHTI ASB
205-98-71, Revision A, dated September 21, 1998.
(ii) Repair any disbonding discovered during the inspection
before further flight.
(6) Within 12 calendar months, remove fin spar, P/N 205-030-899-
001, or -089, or P/N 205-030-846-087, or -089, or P/N 205-032-851-
003, -007, or -009. Replace it with an airworthy fin spar
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, or replace
it with fin spar assembly, P/N 205-530-514-103, as specified in BHTI
ASB 205-98-73, dated September 25, 1998.
(7) Installing fin spar, P/N 205-530-514-103, or a fin spar that
has been approved by the Manager, Rotorcraft Standards Staff,
constitutes terminating action for the requirements of this AD.
(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, FAA, Rotorcraft Directorate,
Rotorcraft Certification Office. Operators shall submit their
requests through a FAA Principal Maintenance Inspector, who may
concur or comment and then send it to the Manager, Rotorcraft
Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Certification Office.
(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 inspections and modifications shall be done in
accordance with Bell Helicopter Textron, Inc. Alert Service Bulletin
204B-98-50, dated October 22, 1998; 205-98-71, Revision A, dated
September 21, 1998; or 205-98-73, dated September 25, 1998, as
applicable. These incorporations by reference were 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.
(f) This amendment becomes effective on September 16, 1999.
Issued in Fort Worth, Texas, on August 4, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-20754 Filed 8-11-99; 8:45 am]
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