[Federal Register Volume 61, Number 179 (Friday, September 13, 1996)]
[Proposed Rules]
[Pages 48441-48443]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-23441]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-SW-06-AD]
Airworthiness Directives; Hiller Aircraft Corporation Model UH-
12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, CH-112, H23A, H-23B, H-23C,
H-23D, H-23F, HTE-1, HTE-2, and OH-23G Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to Hiller Aircraft Corporation
Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, CH-112, H-23A, H-
23B, H-23C, H-23D, H-23F, HTE-1, HTE-2, and OH-23G helicopters, and
Model UH-12D and UH-12E helicopters, converted to turbine engine power
in accordance with Supplemental Type Certificate (STC) No.'s SH177WE
and SH178WE, that currently requires inspections of the control rotor
blade spar tube (blade spar tube) and cuff for cracks, and repair or
replacement as necessary. This action would require inspections of the
blade spar tube and cuff for corrosion or cracks, or elongation,
corrosion, burrs, pitting or fretting of the bolt holes, and repair as
necessary, and would define specific intervals in which the inspections
must be performed. This proposal is prompted by analyses that showed
that the amount of calendar time that elapses between the current
repetitive inspections may allow corrosion to develop. The actions
specified by the proposed AD are intended to prevent separation of the
control rotor blade assembly and subsequent loss of control of the
helicopter.
DATES: Comments must be received by November 12, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 96-SW-06-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137. Comments may be inspected at this location between 9:00
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
The service information referenced in the proposed rule may be
obtained from Hiller Aircraft Corporation, 7980 Enterprise Dr., Newark,
California 94560-3497. This information may be examined at the FAA,
Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas.
FOR FURTHER INFORMATION CONTACT: Mr. Charles Matheis, Aerospace
Engineer, Los Angeles Aircraft Certification Office, FAA, 3960
Paramount. Blvd., Lakewood, California 90712-4137, telephone (310) 627-
5235, fax (310) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 96-SW-06-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules
Docket No. 96-SW-06-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
Discussion
On October 4, 1974, the FAA issued AD 74-21-05, Amendment 39-1990
(39 FR 36855, October 15, 1974), to require, within the next 25 hours
time-in-service (TIS) after the effective date of the AD, unless
already accomplished within the last 25 hours TIS, and thereafter, at
intervals of 100 hours TIS, inspections, and repair or replacement, as
necessary, of the blade spar tube and cuff. On March 24, 1977, the FAA
issued superseding AD 77-07-05, Amendment 39-2862 (42 FR 17868, April
4, 1977) to require, within the next 100 hours TIS after the effective
date of the AD, unless already accomplished within the last 100 hours
TIS, and thereafter, at intervals of 100 hours TIS, inspections of the
blade spar tube and cuffs for cracks, corrosion or excessive wear of
the outboard retention bolts, and repair or replacement, if necessary;
and to establish a service life of 6,860 hours TIS. Then, on June 3,
1977, the FAA issued a revision to Amendment 39-2862 (42 FR 30604, June
16, 1977), AD 77-07-05, which required, within the next 25 hours time-
in-service (TIS) after the effective date of the AD, unless previously
accomplished within the last 25 hours TIS, and thereafter at intervals
not to exceed 50 hours TIS from the date of the last inspection, dye
penetrant inspections of the cuff for cracks, and replacement as
necessary. That action was prompted by a determination made by the FAA
that the data originally furnished as to the availability of
replacement parts was inaccurate. Also, the FAA determined that the
service experience and the use of repetitive dye penetrant inspections
at intervals not to exceed 50 hours TIS, would provide an adequate
level of safety and would avoid the unnecessary grounding of aircraft.
The requirements of that AD are intended to prevent separation of the
control rotor blade assembly and subsequent loss of control of the
helicopter.
Since the issuance of that AD, FAA analyses have shown that the
amount of calendar time that elapses between the current repetitive
inspections may allow corrosion to develop. Additionally, the FAA has
determined that the AD should also apply to those model helicopters
that have been converted to turbine
[[Page 48442]]
engine power in accordance with STC No.'s SH177WE and SH178WE.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model UH-12, UH-12A, UH12B, UH-12C, UH-12D,
UH-12E, CH-112, H-23A, H-23B, H-23C, H23D, H-23F, HTE-1, HTE-2, and OH-
23G helicopters, and Model UH-12D and UH-12E helicopters, converted to
turbine engine power in accordance with STC No.'s SH177WE and SH178WE,
the proposed AD would supersede AD 77-07-05 to require, within the next
100 hours TIS after the effective date of this AD, unless accomplished
within the last 100 hours TIS, and thereafter at intervals not to
exceed 100 hours TIS from the date of the last inspection, or at the
next annual inspection, whichever occurs first, an inspection of the
blade spar tube and cuff for corrosion or cracks, or elongation,
corrosion, burrs, pitting or fretting of the bolt holes, and repair, as
necessary, in accordance with Hiller Aviation Service Bulletin No. 36-
1, Revision 3, dated October 24, 1979.
The FAA estimates that 673 helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately 2 work
hours per helicopter to accomplish the inspection, 1 work hour to
accomplish the repair, and 8 work hours to accomplish the replacement,
if necessary, and that the average labor rate is $60 per work hour.
Required parts would cost approximately $1,000 per cuff, if replacement
is necessary. Based on these figures, the total cost impact of the
proposed AD on U.S. operators is estimated to be $121,140, assuming
after inspection that repairs are necessary on all of the fleet, or
$246,772, assuming inspection of all the fleet and replacement of a
cuff in one-sixth of the fleet is necessary.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-2862 (42 FR
17868, April 4, 1977), and Amendment 39-2917 (42 FR 30604, June 16,
1977) and by adding a new airworthiness directive (AD), to read as
follows:
Hiller Aircraft Corporation: Docket No. 96-SW-06-AD. Supersedes AD
77-07-05, Amendment 39-2862 and Amendment 39-2917.
Applicability: Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-
12E, CH-112, H-23A, H-23B, H-23C, H-23D, H-23F, HTE-1, HTE-2, and
OH-23G helicopters, and Model UH-12D and UH-12E helicopters,
converted to turbine engine power in accordance with Supplemental
Type Certificate (STC) No.'s SH177WE and SH178WE, 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 (e) 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 separation of the control rotor blade assembly and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, unless previously accomplished within the
last 100 hours TIS, and thereafter at intervals not to exceed 100
hours TIS from the date of the last inspection, or at the next
annual inspection, whichever occurs first, inspect the control rotor
blade spar tube and cuff for corrosion or cracks, or elongation,
corrosion, burrs, pitting or fretting of the bolt holes, and repair,
as necessary, in accordance with the Accomplishment Instructions of
Hiller Aviation Service Bulletin No. 36-1, Revision 3, dated October
24, 1979.
(b) After any reaming procedure is accomplished in accordance
with Hiller Aviation Service Bulletin No. 36-1, Revision 3, dated
October 24, 1979, the control rotor blade spar tube (faired and
unfaired) and cuff must be retired at or before accumulating an
additional 2,500 hours TIS after repair or when the current approved
total service life (total service life before repair plus service
life after repair) is reached, whichever comes first.
(c) Fabric covered, metal covered, faired and unfaired control
rotor blades are not interchangeable and must not be intermixed.
(d) For Hiller cuffs, part number (P/N) 36124, used with both
faired and unfaired paddles:
(1) With more than 6,660 hours TIS, remove and replace with an
airworthy part within 200 hours TIS after the effective date of this
AD.
(2) With less than or equal to 6,660 hours TIS, remove and
replace with an airworthy part prior to 6,860 hours TIS.
(3) Without a complete prior service history, within the next 25
hours TIS, unless already accomplished within the last 25 hours TIS
prior to the effective date of this AD, and at intervals not to
exceed 50 hours TIS, perform a dye penetrant inspection of the cuff
in accordance with paragraph G of the Accomplishment Instructions of
Hiller Aviation Service Bulletin, No. 36-1, Revision 3, dated
October 24, 1979. If a crack is discovered, remove the cracked cuff
from service prior to further flight. A cuff for which the prior
service history cannot be documented cannot be used as a replacement
part. Remove from service all cuffs prior to the accumulation of 225
hours total TIS since April 7, 1977.
(e) 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, Los Angeles Aircraft Certification
Office, FAA. Operators shall submit their requests through an FAA
Principal Maintenance Inspector, who may concur or comment and then
send it to the Manager, Los Angeles Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(f) Special flight permits may be issued in accordance with
sections 21.197 and 21.199
[[Page 48443]]
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.
Issued in Fort Worth, Texas, on September 4, 1996.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-23441 Filed 9-12-96; 8:45 am]
BILLING CODE 4910-13-U
