[Federal Register Volume 62, Number 100 (Friday, May 23, 1997)]
[Rules and Regulations]
[Pages 28322-28324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12856]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-SW-06-AD; Amendment 39-10029; AD 97-10-16]
RIN 2120-AA64
Airworthiness Directives; 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
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes 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 UH-12D and UH-12E
helicopters converted to turbine engine power in accordance with
Supplemental Type Certificate (STC) Nos. SH177WE and SH178WE, having a
certain control rotor blade spar tube (blade spar tube) or cuff
installed, that currently requires inspections of the blade spar tube
and cuff for cracks, and repair or replacement as necessary. This
amendment requires 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 defines
specific intervals in which the inspections must be performed. This
amendment is prompted by analyses that show that the amount of calendar
time that elapses between the current repetitive inspections may allow
corrosion to develop. The actions specified by this AD are intended to
prevent separation of the control rotor blade assembly and subsequent
loss of control of the helicopter.
DATES: Effective June 27, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 27, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from Hiller Aircraft Corporation, 3200 Imjin Road, Marina,
California 93933-5101. 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. Charles Matheis, Aerospace
Engineer, Los Angeles Aircraft Certification Office, FAA, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5235, fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 77-07-05,
Amendment 39-2862 (42 FR 17868, April 4, 1977) and Amendment 39-2917
(42 FR 30604, June 16, 1977), which is 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 UH-12D and UH-12E helicopters converted to turbine
engine power in accordance with STC Nos. SH177WE and SH178WE, was
published in the Federal Register on September 13, 1996 (61 FR 48441).
That action proposed to require, within the next 100 hours time-in-
service (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
[[Page 28323]]
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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
The commenter suggests several changes to the Hiller Aircraft
Corporation service bulletin and the proposed rule. These include
changes in the disassembly/reassembly techniques, such as warming of
the cuff to facilitate blade removal, and replacement of certain
lubrication and corrosion prevention materials. The manufacturer and
the FAA have evaluated the suggestions to facilitate disassembly/
reassembly, and the FAA has determined that while helpful, the changes
are not necessary to accomplish the inspections of the AD. Further, the
manufacturer reports no service experience that would indicate a needed
change in lubrication or corrosion protection materials or techniques
as suggested by the commenter. The suggested changes are not adopted.
The commenter also suggests two type design changes that are
outside the scope of the proposal. The FAA will consider these
suggested changes for future rulemaking action.
Finally, the commenter also cites a conflict between the mandatory
replacement times (total service life) in the Hiller Inspection Guide
and those proposed in the proposal. The conflict results because cuff
mandatory replacement time, as specified in the Inspection Guide,
depends on certain combinations of cuff, control blades, and main rotor
blades. This dependency was not adequately considered in the proposal.
Since the FAA did not intend to change these mandatory replacement
times by the proposal, and since it is unnecessary to repeat Inspection
Guide information in the AD, paragraphs (d)(1) and (d)(2) are removed
from this final rule and paragraph (d)(3) becomes paragraph (d).
The FAA has determined that several blade spar tube and cuff part
numbers were omitted from the proposal. The proposed rule's
Applicability has been changed to specify that only helicopters having
a blade spar tube, part numbers (P/N) 36003, 36006, 36129, 36129-25,
36203, 36203-15, 36203-21, or 36209-3, or cuff, P/N 36101-1, 36101-4,
36108, 36115-1, 36115-4, 36115-6, 36115-8, or 36124, installed, are
affected.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. 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 673 helicopters of U.S. registry will be
affected by this AD, that it will 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
will cost approximately $1,000 per cuff, if replacement is necessary.
Based on these figures, the total cost impact of the 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 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 39-2862 (42 FR
17868, April 4, 1977), and Amendment 39-2917 (42 FR 30604, June 16,
1977), and by adding a new airworthiness directive (AD), Amendment 39-
10029, to read as follows:
AD 97-10-16 Hiller Aircraft Corporation: Amendment 39-10029. 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 UH-12D and UH-12E helicopters converted to
turbine engine power in accordance with Supplemental Type
Certificate (STC) No.'s SH177WE and SH178WE, having a control rotor
blade spar tube (blade spar tube), part numbers (P/N) 36003, 36006,
36129, 36129-25, 36203, 36203-15, 36203-21, or 36209-3, or cuff, P/N
36101-1, 36101-4, 36108, 36115-1, 36115-4, 36115-6, 36115-8, or
36124, 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 (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 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
[[Page 28324]]
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 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 cuffs, P/N 36124, 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 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.
(g) The inspections and repair, if necessary, shall be done in
accordance with Hiller Aviation Service Bulletin No. 36-1, Revision
3, dated October 24, 1979. 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
Hiller Aircraft Corporation, 3200 Imjin Road, Marina, California
93933-5101. 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.
(h) This amendment becomes effective on June 27, 1997.
Issued in Fort Worth, Texas, on May 9, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-12856 Filed 5-22-97; 8:45 am]
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