[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]
BILLING CODE 4910-13-U