[Federal Register Volume 64, Number 168 (Tuesday, August 31, 1999)]
[Rules and Regulations]
[Pages 47362-47365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-22077]
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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.
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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
[[Page 47363]]
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 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:
[[Page 47364]]
(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.
[[Page 47365]]
Issued in Fort Worth, Texas, on August 18, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-22077 Filed 8-30-99; 8:45 am]
BILLING CODE 4910-13-U
