[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]


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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).

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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