[Federal Register Volume 62, Number 177 (Friday, September 12, 1997)]
[Rules and Regulations]
[Pages 47933-47934]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-24194]
[[Page 47933]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-SW-04-AD; Amendment 39-10130; AD 97-19-10]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-
64E Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Sikorsky Aircraft-manufactured Model S-64E and S-
64F helicopters, that currently requires initial and repetitive
inspections of the main gearbox assembly second stage lower planetary
plate (plate) for cracks, and removal and replacement of the plate if
cracks are found; and daily inspections of certain main transmission
oil filter packs for magnesium chips, and removal and replacement of
the main transmission if chips are found. The AD also provides for
reworking and re-identifying the plate, as well as establishes a
retirement life for the plate, including those that have been reworked
and re-identified. This amendment requires, for Model S-64E
helicopters, inspections and rework of the plate and establishes a new
retirement life for the plate. This amendment is prompted by the type
certificate holder's reports that four plates were discovered to have
cracks, three of which had been reworked in accordance with the
existing AD. The actions specified by this AD are intended to add
another plate to the applicability of the AD, remove the requirements
of AD 77-20-01 for the Model S-64F and prevent failure of the plate on
the Model S-64E due to fatigue cracking, which could lead to failure of
the main gearbox and subsequent loss of control of the helicopter.
DATES: Effective October 17, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 17, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from Erickson Air-Crane Co., 3100 Willow Springs Rd., P.O. Box
3247, Central Point, OR 97502. This information may be examined at the
FAA, Office of the Assistant Chief Counsel, 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: Mr. Uday Garadi, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5157, fax
(817) 222-5783.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 77-20-01,
Amendment 39-3045 (42 FR 51565, September 29, 1977), which was revised
by Amendment 39-3064 (42 FR 56600, October 27, 1977), and is applicable
to Sikorsky Aircraft-manufactured Model S-64E and S-64F helicopters,
was published in the Federal Register on October 11, 1996 (61 FR
53339). That action proposed to require, at 1,300 hours time-in-service
(TIS), a fluorescent magnetic particle inspection of the plate, part
number (P/N) 6435-20229-102, for cracks, replacement of the plate if a
crack is found, and reworking the plate if no crack is found. The
action also proposed to require, at 1,500 hours TIS, and thereafter at
intervals not to exceed 70 hours TIS, for reworked plate, P/N 6435-
20229-102, reidentified as P/N 6435-20229-102-TS-107 after rework, and
for plate, P/N 6435-20229-104, a borescope inspection for cracks and
replacement of the plate if a crack is found. Finally, it was proposed
that these part-numbered plates be retired upon reaching 2,600 hours
TIS.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter states that the AD should not be applicable to Model
S64F helicopters as in the existing AD because of differences in part
numbers between that model helicopter and the Model S64E helicopter.
The FAA concurs, and did not include Model S64F helicopters in the
applicability portion of the proposal, nor in this final rule.
A second commenter addressed restricted category Model CH54A
helicopters. This AD does not affect those model helicopters--only
Model S64E helicopters. The FAA anticipates issuing another AD
applicable to Model CH54A helicopters at a later date.
After careful review of the available data, including the comments
previously noted, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed except for adding
``reidentified as'' prior to P/N 6435-20229-102-TS-107, and ``after
rework'' after that P/N. The FAA has determined that these non-
substantive changes will neither increase the economic burden on any
operator nor increase the scope of the AD.
The FAA estimates that 8 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 8 work hours per
helicopter to accomplish the inspections and 56 hours to remove and
replace the main gearbox assembly, if necessary, and that the average
labor rate is $60 per work hour. Required parts will cost $8,000 per
helicopter. Based on these figures, the total cost impact of this AD on
U.S. operators is estimated to be $94,720; $3,840 to accomplish the
inspections, and $90,880 to replace the plate in the main gearbox
assembly in all 8 helicopters, if necessary.
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:
[[Page 47934]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-3045 (42 FR
51565, September 29, 1977) and 39-3064 (42 FR 56600, October 27, 1977),
and by adding a new airworthiness directive (AD), Amendment 39-10130,
to read as follows:
97-19-10 Erickson Air-Crane Co.: Amendment 39-10130. Docket No. 96-
SW-04-AD. Supersedes AD 77-20-01, Amendment 39-3045 and Amendment
39-3064.
Applicability: Sikorsky Aircraft-manufactured Model S-64E
helicopters, with main gearbox assembly second stage lower planetary
plate (plate), part number (P/N) 6435-20229-102, reidentified as P/N
6435-20229-102-TS-107 after rework, or P/N 6435-20229-104,
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
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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the plate due to fatigue cracking, which
could lead to failure of the main gearbox and subsequent loss of
control of the helicopter, accomplish the following:
(a) For plate, part number (P/N) 6435-20229-102 and P/N 6435-
20229-102-TS-107, at 1,300 hours total time-in-service (TIS),
inspect and rework or replace the plate, as appropriate, in
accordance with the Accomplishment Instructions, paragraph 2A.,
steps (1), and (3) through (11), of Erickson Air-Crane Co. Service
Bulletin No. 64B35-7C, dated November 8, 1995.
(b) For any plate, P/N 6435-20229-102, that has been reworked
and identified with ``TS-107'', and for plate, P/N 6435-20229-104,
at 1,500 hours TIS and thereafter at intervals not to exceed 70
hours TIS, inspect the plate in accordance with the Accomplishment
Instructions, paragraph 2B., step (1), of Erickson Air-Crane Co.
Service Bulletin No. 64B35-7C, dated November 8, 1995. If a crack is
found, replace the main gearbox assembly with an airworthy assembly.
(c) This AD revises the airworthiness limitation section of the
maintenance manual by establishing a retirement life of 2,600 hours
TIS for the main gearbox assembly second stage planetary plate, P/N
6435-20229-102, reidentified as P/N 6435-20229-102-TS-107 after
rework, and P/N 6435-20229-104.
(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 Certification Office,
Rotorcraft Directorate, FAA. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Rotorcraft Certification
Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Certification Office.
(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 inspections and rework or replacement, as necessary,
shall be done in accordance with Erickson Air-Crane Co. Service
Bulletin No. 64B35-7C, dated November 8, 1995. 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 Erickson Air-Crane Co., 3100 Willow Springs Rd., P.O.
Box 3247, Central Point, OR 97502. Copies may be inspected at the
FAA, Office of the Assistant Chief Counsel, 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 17, 1997.
Issued in Fort Worth, Texas, on September 5, 1997.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-24194 Filed 9-11-97; 8:45 am]
BILLING CODE 4910-13-U
